Opening Ceremony will be held on Thursday, March 4 through Zoom on LIVE. At the opening ceremony, AJCPP2021 begins with the opening address and welcoming address.
| Date & Time | 10:10 ~ 10:30 / March 4 (Thursday), 2021 |
| Attendees | Registered AJCPP2021 participants |
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Secretariat of AJCPP2021 The Korean Society of Propulsion Engineers Copyright © KSPE. All rights reserved. |
 
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Dear Colleagues,
First of all, I would like to express my sincere thanks to all members of the AJCPP for your active participations.
Even though we could not offer you a banquet or a tour in this year, your contribution during the conference was so enormous that we can achieve the very successful AJCPP 2021.
Also, I would like to appreciate the LOC and IOC members for their great efforts; they have worked so hard for 2 years in order to prepare the successful virtual AJCPP 2021.
The Next 11th AJCPP will be held in Kanazawa, Japan, two years later in 2023.
The city of Kanazawa is known to be one of the famous historical cities in Japan and was designated a UNESCO Creative Cities Network (UCCN).
Therefore, I hope we can see each other at the venue in Kanazawa without COVID-19 in 2023.
Youngbin Yoon
Chair, AJCPP2021
Professor, Seoul National University
AJCPP2021 secretariat (secretariat@ajcpp2021.org)
– Cancellation Policy
Cancel request after February 29, 2020 100% Cancellation Penalty will be charged for whole stay reserved.
| Hotel Name (Grade) | Room Type | Bed Type | Breakfast (per person) |
Venue | ||
|---|---|---|---|---|---|---|
| Single | Double | Twin | ||||
| Sheraton Grand Hotel (☆☆☆☆☆) |
Deluxe | KRW 160,000 | KRW 160,000 | – | KRW 24,200 | 3 min. on foot |
* All room rates are included 10% service charge and 11% government tax.
– Cancellation Policy
1 night penalty will be charge on the no show and cancellation can be made 6pm, 3 days before the arrival date.
* The hotel will consider the booking to have been cancelled when the guest who has made a reservation for over
One day has not check-in on the first day of the reservation
| Hotel Name (Grade) | Room Type | Bed Type | Breakfast (per person) |
Venue | ||
|---|---|---|---|---|---|---|
| Single | Double | Twin | ||||
| Oakwood Premier Incheon (☆☆☆☆☆) |
Superior | – | KRW 175,450 | – | KRW 29,000 | 5 min. on foot |
* All room rates are included 10% service charge and 11% government tax.
– Cancellation Policy
1. When cancelled 2 days prior to arrival: No cancellation charge.
2. When cancelled before 2 day on the day of arrival: 100% of the first days room charge.
3. If you are no-show on the arrival day, or there are no prior notice: 100 % of the first days room charge..
| Hotel Name (Grade) | Room Type | Bed Type | Breakfast (per person) |
Venue | ||
|---|---|---|---|---|---|---|
| Single | Double | Twin | ||||
| RAMADA Incheon (☆☆☆☆) |
Premier | – | KRW 88,000 | KRW 99,000 | Free | 15 min. on foot |
* All room rates are included 10% service charge and 11% government tax.
Makoto Yoshida is currently Director of JAXA Kakuda Space Center since April 2015. He earned his Master of Engineering from University of Tokyo in 1985, and his PhD in Engineering from Tohoku University in 1999. In 1985, he became a researcher of National Aerospace Laboratory (NAL), the predecessor of JAXA, and he engaged in research and development of the liquid oxygen turbopump for LE-7 engine, the first stage rocket engine of all domestic H-2 rocket. He stayed in Massachusetts Institute of Technology as a visiting scientist from 1990 to 1992 in high temperature materials Lab. The current interests are wide range of future space propulsion systems such as reusable rocket engines, air-breathing engines, and engines for planetary exploration.
Kakuda Space Center is a research and development hub for JAXA’s space propulsion technology. The center is used for various tasks from research of fundamental technologies to development and tests of rocket engines. The center had engaged in R&D and test work on LE-5 engine, Japan’s first LOX/LH2 engine which settled the basis of Japan’s large-sized rocket engines. The center is now developing the upgraded LE-5B-3 engine, and the most advanced LE-9 engine for Japan’s Next Generation Launch Vehicle H3. The research of reusable rocket engine and scramjet engine aiming at fully reusable future launch system are also investigated. The facilities are open to private businesses, universities, and foreign space agencies such as NASA. The presentation will describe the future research and development of space propulsion system, following the history of research and development at the Kakuda Space Center.
Space propulsion system is essential for orbit transfer and attitude control of a spacecraft. Depending on its application, typical thrust level of space propulsion system ranges from tens to thousands of Newton. Conventional space propulsion systems have been built on monopropellant hydrazine or monomethyl hydrazine-nitrogen tetroxide hypergolic bipropellant. These hydrazine-based propellants are highly toxic and carcinogenic, which incur high cost in system development and testing to protect the personnel from the toxic fume of the propellants. Investigation on nontoxic green propellants for space propulsion system has been gaining momentum in Europe and the US since 1990. The author would like to present the research activity of Rocket Lab KAIST on green propellants for the past twenty years. Hydrogen peroxide and ammonium dinitramide (ADN) monopropellants with their decomposition catalyst will be examined. Development of hydrogen peroxide monopropellant thruster and their system implementation will be discussed. Design, fabrication and firing test of the thrusters will be presented. For orbit transfer of spacecraft, higher specific impulse thruster with high thrust level is necessary. Bipropellant thruster with hydrogen peroxide as an oxidizer was developed and tested for this purpose. Finally, hypergolic bipropellant thruster with hydrogen peroxide and fuel with additive was developed and tested. Comparison of hydrogen peroxide and conventional propellants will be discussed.
According to research, curved compression system has advantages in reducing total-pressure loss, shortening compression length, avoiding boundary layer separation, improving non-design point performance, reducing drag, tolerating non-uniform coming flow. Therefore, curved compression inlet gradually draws attention, explorations and detailed researches have been carried out for design method, performance and application of such flow field, and rich achievements have been made.
There are two kind of inverse design methods. The design idea and process of the first kind of inverse design are introduced, namely design for the whole compression surface based on existing flow parameter distribution. The focus of flow field design is the design of one or more curved shock waves and obviously the solution is not unique.
The second kind of inverse design is introduced, namely design for compression surface shape and the whole compression flow field based on the specified pressure distribution on compression surface or design for geometric shape of compression surface and the whole curved shock wave compression flow field based on the specified compression surface deceleration rule.
With the increasing inward turning inlet research, design of axisymmetric reference flow field has become a key problem. The process and details of designing axisymmetric reference flow field with inverse tangent pressure rising rule of wall, inverse tangent decelerating rule of wall and other method by fully using the second kind of inverse design method are introduced. A new method is provided for designing excellent-performance inward turning inlet.
The design processes, model experiments and partial experiment results of these inlets for design of hypersonic two dimensional inlet, hypersonic axisymmetric inlet, hypersonic sidewall compression inlet and hypersonic inward turning inlet with the inverse design methods, are introduced.
In order to adapt to the needs in wide Mach number working range, both the concept of curved shock wave curved compression surface and concept of adaptive variable geometric elastic curved compression surface are proposed. The performance advantages and future development of this new design concept are discussed.
