japanese space development(part 2)

Japanese
Space Development (Part 2)
Textbook for Space Development
Japan Aerospace Exploration Agency
Copyright © 2016 Japan Aerospace Exploration Agency All Rights Reserved.

2Copyright © 2016 Japan Aerospace Exploration Agency All Rights Reserved.
Overview（1/2）
Title Japanese Space Development (Part 2)
Overview About the International Space Station that Japan, America, Russia,
EU and Canada participate, and Japanese rockets that has world-
class high reliability.
Purpose
of This Unite
Improve knowledge
This Unit for Administrative Officer, Engineer (Introduction)
Requirement
for Taking
This Unit
None

3
When
You Master
This Unit...
 You can understand solid propellant rocket and liquid propellant
rocket. Solid propellant rocket was developed independently in
Japan. Liquid propellant rocket started by introduction of
technology from foreign countries and was established our own
technology in stages.
Overview（2/2）

4
• 3. Manned Space Development
3.1 International Space Station “ISS”
3.2 Japanese Experiment Module “Kibo”
3.3 H-II Transfer Vehicle
“KOUNOTORI”(HTV)
• 4. Space Transportation Systems Development
4.1 Japanese high reliability rocket
4.2 Transportation Systems Development
4.3 Solid Propellant Rockets
4.4 Liquid Propellant Rockets
• 5. Conclusion
Contents

3. Manned Space Development
5（C）JAXA/NASA
International Space Station “ISS”
H-II Transfer Vehicle (HTV)
Japanese Experiment Module “Kibo”

・Supplying the robot arm
・Supplying experiment module
・Supplying solar battery paddles
・Transport of goods by spaceship
・Transport of crew and goods
by spaceship
・Supplying habitation module
・Supplying Oxygen
(ended on 2014)
3.1 International Space Station “ISS”
6Cooperation agency of the ISS project
International Space Station
(http://www.jaxa.jp/projects/pr/brochure/pdf/02/station01.pdf)
• ISS is a international project cooperating 15 countries.
• Using special environment at an altitude 400km in space, Earth and
astronomical observation, experimentation and study have been carried
out.

7
• Experiment module developed by Japan.
• Largest of habitable modules in ISS.
• There are facility for experiment and observation in out of “Kibo” and own
“Airlock” for taking in and out from “Kibo” and “Robotic Arm”.
“KIBO” appearance
①Experiment Logistics Module
Pressurized Section
②Pressurized Module
The experimental facility using microgravity
environment. It’s kept 1 atm, and crews can
experiment easy.
③Remote Manipulator System (Robotic
Arm)
④Exposed Facility
In “Kibo” it can Earth and astronomical
observation and demonstrate space
technology.
Pressurized Module

8
Characteristics of Kibo
• 10-6G microgravity environment. (Approximately 1/1,000,000 of ground.)
• It can observe the astronomical bodies without passing through the atmosphere.
• It can observe ultraviolet rays and X-rays directly that are absorbed by air and
difficult to observe on ground.
• Features of the exposed Facility : Because bus equipment has already been
prepared, you can observe or experiment only development mission equipment.
Application fields of Kibo
• Support the healthy life expectancy society.
Studies using the acceleration phenomenon of the age-related changes, Development of medicine with high
quality protein crystals.
• Achieve a prosperous and safe and secure living.
Earth observation help for environmental change prediction and wide area disaster monitoring.
• Enhance the competitiveness of enterprises by making things.
Generation of large single crystal that is next-generation high-performance semiconductor material,
Elucidation of the mechanism of higher-order molecular structure change.
• Aims to unexplored space
Technology development for further long-term space stay such as water reclamation system, astronaut of
telemedicine system and Lightweight next-generation space suit.
• Open up a new knowledge area
Scientific research rooted in the intellectual curiosity of the human race such as all-sky of monitoring by the X-
ray and elucidation of the mechanism by which ice crystals grow.
【Reference URL about utilizing “KIBO”(Japanese)】
http://iss.jaxa.jp/
Reference : “Kibo” using summary

3.3 H-II Transfer Vehicle “KOUNOTORI” (HTV)
9
• After retirement of the space shuttle, “KOUNOTORI” works as a way to
transport large in or out-board equipment to ISS.
• High reliability as fail-safe (multiple redundant configuration).
“KOUNOTORI”
appearance
KOUNOTORI module
Progress KOUNOTORI
Dragon
(Normal)
Dragon
(Expansion)
Cygnus
(Normal)
Cygnus
(Expansion)
Pressurized part
Unpressurized part
Propellant
Various transfer vehicle (c) Wikipedia

1
0
(C)JAXA,NASA,NHK
Grand sum of Japanese liquid propellant rocket
H3 Rocket
4. Space Transportation Systems Development
Solid Propellant Rocket
Launching small satellites
Epsilon Rocket
Japanese first launching a satellite
L-4S Rocket
A pioneer in
Japanese Rocket,
Hideo Itokawa
Liquid Propellant Rocket
Cost greatly reduced
H-II A Rocket
Domestically
Liquid Propellant Rocket
H-II Rocket
Japanese first liquid propellant rocket
N-I Rocket

11
Even if satellites have high-performance
sensor, it becomes possible to perform its
ability at the maximam when injected to
predetermined orbit. Japan has world class
development and operating results of liquid
propellant rocket and solid propellant rocket.
We have success 30 times launching of H-IIA
and H-IIB continuously. Its operating result is
world top class.
Japanese H-IIA and H-IIB having operating
track record with the highest level in the world.

12
H-IIA
H-IIA H-IIB Sum
Launch ability to
geostationary transfer orbit
4t
(6t maximum)
8t
(to HTV orbit is 16.5t)
The number of launch 30 5 35
The number of the
successful launch
29 5 34
Launch success rate 96.7% 100% 97%
As of February 2016
Launch success rate of
Japanese main rocket,
H-IIA and H-IIB is
97.1%.
In general, launch
success rate 95% is
high reliability.
Launch success rate
of H-IIA and H-IIB is
world top class!
➀ Launch success rate
• In 2001 Success in the launch of the H-IIA launch vehicle no.1.
• In 2009 Success in the launch H-II Transfer Vehicle “KOUNOTORI” (HTV) by H-
IIB test flight 1.

13
② On-time launch
On-time launch result of H-IIA and H-IIB
H-IIA and H-IIB are not only world top class success launch rate, bat
also have result of on-time launch that is launching at scheduled time.
※except postponed due to weather and failure of the payload side.
H-IIA
H-IIB
Postponement
Ontime
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30
1 2 3 4 5
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Ontime
Postponement
Postponement
Postponement
Postponement
Postponement
Ontime
Ontime
Ontime
Ontime
Ontime

14
4.2 Transportation Systems Development
Succeeded launching OHSHUMI by L-4S rocket in 1970.
The fourth nation as launching Satellite onto orbit in the world.
After that, it launches science satellites mainly.
Started N-I rocket development in 1970.
Succeeded launching “Engineering Test Satellite I” to Low Earth Orbit.
After that, it launches large actual use satellites mainly.
Solid propellant rocket
Liquid propellant rocket
• There are two kinds of propulsion systems of rocket that are solid propellant
rocket and liquid propellant rocket.
• Japan is developing and operating liquid propellant rocket H-IIA/B and solid
propellant rocket Epsilon as main rockets.
• There are each futures, these are properly used by launching satellite or injection
orbit.

15
“HAYABUSA” :
Launched by M-V-5
“OHSUMI” :
Launched by L-4S-5
➀ Japanese Solid Propellant Rockets Tree
Name of rockets Pencil L-4S M-4S M-3C M-3H M-3S M-3SⅡ M-V-5 Epsilon
Height (m) 23 cm 16.5 23.6 20.2 23.8 23.8 27.8 30.8 24.4
Weight (ton) 9.4 43.6 41.6 48.7 48.7 61 140.4 91
Launch ability to low orbit (kg) -- 26 180 195 300 300 770 1,850 1,200
Ratio of payload to total
rocket weight (%)
-- 0.28 0.41 0.47 0.62 0.62 1.26 1.32 1.33
Guidance control -- No No Second stage Second stage 1&2 stages 1&2 stages 1&2&3 stages 1&2&3 (option)
“HISAKI” :
Launched by
Epsilon

② Epsilon Rocket
10m
20m
30m
Test rocket launch
(at Uchinoura Space Center on September 2013)
M-V Epsilon
Length 30.8 m 24.4 m
Diameter (main) 2.5 m 2.5 m
Propellant
Third Solid Solid
Second Solid Solid
First Solid Solid
Orbit injection ability
・Low orbit around the earth
・Sun-synchronous orbit
・Orbit injection accuracy
1,800kg
－
－
1,200kg
450kg
As well as liquid
Working period at range
(From setting first shooting place to the
next day of launched)
42 days 9 days
From satellite last access to
launch
9 hour 3 hour
 Solid propellant rocket for launching small
satellite aimed at meeting user’s desired
more quickly.
 In developing Epsilon rocket, we used M-V
and H-IIA technology maximum.
 It can be added small propulsion system.
Therefore it can response flexibly to
customer requirements such as introduce
orbit and orbit injection accuracy.
 Succeed launch first rocket on September 14,
2013. Spectroscopic Planet Observatory for
Recognition of Interaction of Atmosphere
“HISAKI” was launched.
 Now, we are developing enhanced Epsilon
aiming to improve the performance.
16

③ Technology of Epsilon development
17
 Using technology accumulations maximum that has been obtained in the rockets
development for 60 years.
 By adopting innovative technology aggressively, we realize user friendly operation.
Kick stage improvement
The third stage improvement
Third
First
Second
H-IIA/B rocket
(Operating now)M-V Rocket
(Operated until 2005)
Epsilon rocket
Inheritance and
development of
technology of solid rocket
(SRB-A, Electronics and parts etc.)
Standardization of equipment
and parts of H-IIA.
 Realization of simple
launch control
 Adopting low-cost
structure and avionics
technology.
 Fairing improvement.
etc.
Demonstration advanced
transport system technology

For second rocket, develop performance improvement. (Improvement of
launch capability, Expansion of the launch possible satellite size
(Satellite envelope region)) Therefore, it is possible to offer launch
opportunities more wide range users.
This is planning to apply to the launch of Exploration of energization and
Radiation in Geospace in 2016 fiscal year.
④ Enhanced Epsilon
18
Overview of enhanced Epsilon
Enhanced
⇒Expansion satellite
envelope region
Current
Fairing
First stage First stage
Fairing
Increasing size of the second
motor (Out of Fairing)
The second motor
(Out of Fairing)
⇒Improve of
launching ability

19
※1 Diameter of core rocket part.
※2 GTO：Geostationary Transfer Orbit
50m
20m
40m
① Japanese Liquid Propellant Rockets Tree
Rocket name N-I N-II H-I H-II H-IIA H-IIB
Stages 3 3 3 2 2 2
Height (m) 32.6 35.4 40.3 50 53 56
Diameter (Core)(m)※1 2.4 2.4 2.44 4 4 5.2
Launch ability to GTO(t)※2 0.25 0.7 1.1 4.0 4.0 8.0
First launched year 1975 1981 1986 1994 2001 2009
Number of Succeed /
Launch
6/7 8/8 9/9 5/7 29/30 5/5

Rocket
Number of
Succeed / Launch
Succeed rate(%)
Falcon9 16 / 16 100%
Atlas V 52 / 53 98.1%
Ariane 5 51 / 52 98.1%
H-IIA/B 31 / 32 96.9%
Delta4 28 / 29 96.6%
Chang Zheng3 68 / 73 93.2%
Soyuz CSG 10 / 11 90.9%
Proton M 79 / 88 89.8%
20
② H-IIA Rocket
 Large rocket that enable free space activities.
 Launch success rate and on-time launch rate are world's highest level.
 Especially on-time launch rate is important for achievement of user plan.
In addition, launching without trouble indicate high reliability.
 It has ever launched satellites of Japan, Korea, Canada, Australia.
 On top of that, it can equip small satellite as a sub-satellite with main
payload.
 There are two types of rocket depending on the satellite weight and injected
orbit. Fairing is selectively used from several types depending on the size
and number of satellites.
 For the purpose of expansion of the base of space development and utilization
and development of human resources responsible for space development of
the next generation, taking advantage of the excess capacity of H-IIA,
JAXA offer announcement of opportunity of launching small satellite as
“piggyback” for private enterprises and universities.
4S type faring
5S type faring
Type H2A202 H2A204
Launch ability to GTO
ΔV=1800m/s
about
4.0ton
about
6.0ton
▽Main rocket launch success rate (As of2015/3/31)
▽Image of Micro Sat as ”piggyback”

21
③ H-IIB Rocket
H-IIB Rocket H-IIA204type
(reference)
All length
All mass
About 57m
About 530t
About 53m
About 445t
First
stage
Tank diameter
Propellant mass
Engine
Thrust
5.2m
176t
LE-7A×2 parts
112t×2
4m
100t
LE-7A×1part
112t
Second
stage
Tank diameter
Propellant mass
Engine
Thrust
4m
16.7t
LE-5B×1 part
14t
4m
16.7t
LE-5B×1 part
14t
SRB-A
Propellant mass
Number of
mounting machine
66t/machine
4 machines
66t/machine
4 machines
All length
about
56m
Faring for HTV
Second stage
Liquid hydrogen tank
Second stage
Liquid oxygen tank
Second stage
engine (LE-5B)
First stage engine
(LE-7A×2 parts)
HTV
Solid Rocket
booster (SRB-A)
First stage
diameter 5.2m
H-IIB-4 rocket movement H-IIB-4 launch
 For the purpose of launching ISS resupply vehicle
“KOUNOTORI” and to strengthen International
competitiveness, we developed H-IIB based on H-IIA.
 Since test rocket was launched on September 11, 2009, we
succeed launch at scheduled day/hour/second in 5
times continuous. (Except for the postponement due to
weather)
 Now, H-IIB has been launching as launch transport service
by private company MHI, since vehicle No.4 in 2013,
as well as H-IIA.
First stage
Liquid oxygen tank
First stage
Liquid hydrogen tank

22
④ H3 Rocket
 ”H3” project is Japanese rocket development project.
 It’s a rocket to launch large satellite and it takes over H-IIA and H-IIB
that is operated now.
 Aiming to launch the test vehicle in the 2020 fiscal year.

23
⑤ The aim of the H3 Rocket
 Developing to realize the voice of customer primarily.
 World-class reliability and price, Focus on flexible service.
 To realize such a system, summing-up rocket technology,
and merging specialty Japanese technology.
 Easy-to-use with ease.
 Support utilizing space in the future.
 For the almost of the people around the world.

24
⑥ Concept of H3 Rocket
• Drastic cost reduction：
– Module of the system, line production. (Standardization of core of
rocket)
– Utilizing private products including electronic component.
• High reliability：
– Adopt a reliable development approach For the first-stage engine.
– System configuration of the avionics that pursues of fault tolerance.
• Flexible service：
– Faster service by short term from order to launch.
– More launch opportunities by half of the interval.
– Shortening of work period of satellite at launch site.

Copyright © 2016 Japan Aerospace Exploration Agency All Rights Reserved.25
⑦ Basic system of H3 Rocket
202 204
H-IIA H-IIB
 Aiming to sun-synchronous
orbit ※ 4tons or more
 Aiming to about half cost
of H-IIA
 Aiming to geostationary transfer orbit 6.5
tons or more（Cover the majority of the
satellite demand by single launch）
※500km circle orbit
The new first-stage engine（LE-9）
Thrust 150t X 2 or 3 switching
Improved solid rocket booster
（SRB-3）
The average thrust 220t X 0-4
Simple binding separation
mechanism
Large satellite faring
Improved two-stage engine
（LE-5B-3） Thrust 14t X 1
 length：About 63m
 Diameter of core rocket：About 5.2m
 Diameter of solid rocket booster： About 2.5m
 Service for customer
 Launching environment：More than the world standard
 Duration of up to launch from order：More than the world standard

26
• Rocket identification name
H3-abc a： Number of LE-9 (2,3) b： Number of SRB-3 (0,2,4) c：Faring size (S,L)
H3-22L
H3-32L
H3-22S
H3-32S
H3-24LH3-24SH3-30LH3-30S

 By shortening of the launch site maintenance, we provide launch
service for more users with more flexibility.
Comparison of the launch site maintenance work period
▽ H-IIA Rocket ： 53 days （the shortest result）
△ H3 Rocket： About half of the H-IIA rocket
27
Maintenance and inspection of
post-launch
Rocket
assembly
Functional
check
Satellite
equipped
Count
down
【Policy】
Simple binding of the solid rocket
booster. etc.
【Policy】
・Automatic check
・Elimination of the inspection device connection.
【Policy】
・Reduction of damage by launch.
・Functional allocation review of inter-equipment.

28
⑧ Synergy of H3 and Epsilon
H3
Epsilon
Maximum
commonalization
・Motor case
・Propellant
・Combustion pattern
etc.
SRB-3
Fist stage
motor
 By more commonalization of H3 rocket
and Epsilon rocket, reduce the
manufacturing cost.
 Aiming to stable low price when launch a
large satellite using H3, or small satellite
using Epsilon.

5. Conclusion
29
【Space crafts development】
• Japan succeeded in actual use satellites field such as earth observation
satellites, communication and positioning satellites and meteorological
satellites and science exploration satellites field such as planetary exploration,
asteroid exploration and astronomical observation. And Japan became a world
top class space developed country.
• These space crafts development used results of on-orbit element technology
test by engineering test satellites. Thus, we adopted schemes developing
actual use satellites absolutely.
【Transfer vehicles development】
• Japan develop and operate “Epsilon” for small satellites and “H-IIA” for large
satellite launch.
• Furthermore, we are developing new main rocket “H3” as a next rocket of “H-
IIA”, and we are planning launching it in 2020.
We can provide know-how of satellite developing
and launching service of rocket that has
Investment performance of world top level.

Textbook for Space Development March 2016: First Edition

japanese space development(part 2)

Recommended

Recommended

More Related Content

What's hot

What's hot (20)

Similar to japanese space development(part 2)

Similar to japanese space development(part 2) (20)

More from hepta-sat

More from hepta-sat (6)

Recently uploaded

Recently uploaded (20)

japanese space development(part 2)

Editor's Notes