Japan Fiscal Year 2010 Spring Launch Season
Launch Plan ofVenus Climate Orbiter (PLANET-C) /Small Secondary Satellites
by H-IIA Launch Vehicle No. 17 (H-IIA F17)

March 2010

MITSUBISHI HEAVY INDUSTRIES, LTD.
JAPAN AEROSPACE EXPLORATION AGENCY (JAXA)(Independent Administrative Agency)

Table of Contents
1. Overview
1.1 Organization and Person in Charge of Launch
1.2 Objectives of Launch
1.3 Launch Vehicle and Payloads
1.4 Launch Window (Day and Time)
1.5 Facilities for Launch

Page
1
1
1
2
2
2

2. Launch Plan
2.1 Launch Site
2.2 Launch Responsibility Sharing
2.3 Launch Organization
2.4 Launch Vehicle Flight Plan
2.5 Major Characteristics of the Launch Vehicle
2.6 Outline of the Main Payload “Venus Climate Orbiter (PLANET-C)”
2.7 Outline of the Small Secondary Payloads (Piggyback Payloads)
2.8 Securing Launch Safety
2.9 Correspondence Method of Launch Information to Parties Concerned

3
3
3
5
8
8
8
9
9
10

3. Launch Result Report

10[List of Figures]
Figure-1: Map of Launch Facilities
Figure-2: Launch Vehicle Flight Trajectory
Figure-3: Configuration of the Launch Vehicle (H2A202 Type)
Figure-4: On-orbit Configuration of PLANET-C
Figure-5: Overview and Loading Position of the Small Secondary Payloads
Figure-6: Access Control Areas for Launch
Figure-7: Impact Areas of the Launch Vehicle Jettison

11
13
15
18
19
20
21

[List of Tables]
Table-1: Launch Vehicle Flight Plan
Table-2: Major Characteristics of the Launch Vehicle
Table-3: Major Characteristics of PLANET-C
Table-4: Outline of the Small Secondary Payloads

12
14
16
19

1.

Overview
The Japan Aerospace Exploration Agency (hereinafter referred to as “JAXA”), an independentadministrative agency, is scheduled to carry out the launch of the Venus Climate Orbiter
PLANET-C (hereinafter referred to the “PLANET-C”) using the H-IIA Launch Vehicle No. 17(hereinafter referred to the “H-IIA F17”) in the spring launch season in Japanese Fiscal Year2010. JAXA also offers an orbit injection opportunity to five small secondary payloads(piggyback satellites) by utilizing the excessive launch capability.
This document explains how the launch plan will be carried out: from the time of the liftoff ofthe H-IIA F17 through the confirmation of the PLANET-C separation from the second stage ofthe launch vehicle and separation signal transmission to the small secondary payloads.
The launch this time will be performed by MITSUBISHI HEAVY INDUSTRIES, LTD(hereinafter referred to as “MHI”) as a launch and transportation service, and JAXA will be
responsible for launch safety control and management.

1.1

Organization and Person in Charge of Launch(1) Launch Execution(A) Launch implementation organization
MHI
President: Hideaki Omiya
Address: 2-16-5, Konana Minato-ku, Tokyo, 108-8215 Japan(B) Person in charge of launch implementation
Takashi Maemura
技監・技師長, MHI Nagoya Aerospace Systems Works(2) Launch Safety Control and Management(A) Launch safety control and management organization
JAXA
President: Keiji Tachikawa
Address: 7-44-1 Jindaiji Higashi-machi, Chofu-shi, Tokyo, 182-8522 Japan(B) Person in charge of launch safety control and management
Norio Sakazume
JAXA Director of the Tanegashima Space Center

1.2

Objectives of Launch
To inject the main payload, the Venus Climate Orbiter “PLANET-C,” into its scheduled orbit
by the H-IIA F17, and to provide an orbit injection opportunity to small secondary payloads
using excessive launch capabilities.

-1-1.3 Launch Vehicle and Payloads- H-IIA F17
H-IIA 202
Four-meter diameter fairing- Payloads: Main Payload: Venus Climate Orbiter “PLANET-C”
Small Secondary Payloads:
Small Solar Power sail Demonstrator “IKAROS”
UNITEC-1
WASEDA-SAT2 (*1)
KSAT (*1)
Negai*” (*1)

One unit
One unit
One unit
One unit
One unit
One unit
One unit(*1: Those satellites will be packed and loaded to the J-POD, JAXA Picosatellite Orbital Deployer)

1.4 Launch Window (Day and Time)
Launch Vehicle
Type

Scheduled
Launch Day

LaunchTime

Time of the Launch Vehicle
JettisonLaunchWindow-

H-IIA Launch
Vehicle No. 17(H-IIA F17)

May 18 (Tue),2010

6:44:14BetweenMay 19 (Wed)thru June 3 (Thu),
2010-(After liftoff)
Solid rocket boosters: about 6 to
10 minutes after liftoff
Payload fairing: about 11 to 26
minutes
First stage: about 15 to 32
minutesDates and times are Japan Standard Time.
Launch time will be determined day to day if the launch is delayed.

1.5

Facilities for Launch
Figure-1 shows the facilities of JAXA and organizations that will support JAXA for launch
operations.

-2-

2.

Launch Plan

2.1 Launch Site
(1) JAXA Facilities(a) Tanegashima Space Center
Oaza-Kukinaga, Minamitane-machi, Kumage-gun, Kagoshima, Japan(b) Ogasawara Downrange Station
Kuwanokiyama, Chichijima, Ogasawara-mura, Tokyo(c) Christmas Downrange Station
Christmas Island, Republic of Kiribati(2) Non-JAXA Facility(a) Goddard Downrange Station
NASA Goddard Space Flight Center
2.2 Launch Responsibility Sharing
The following is the major responsibility sharing between JAXA and MHI with regard to thislaunch.
(1) MHI Responsibility
MHI is to conduct the launch as a launch provider being commissioned by JAXA under alaunch service agreement to inject the main payload, PLANET-C, into its scheduled orbit.
Also, MHI will transmit separation signals to the small secondary payloads at a predeterminedtime.
(2) JAXA Responsibility
JAXA develops the PLANET-C and commissions the launch transportation service of the
PLANET-C and small secondary payloads to MHI. JAXA also conducts interface control
between the small secondary payloads and the launch vehicle with the small secondary payload
developers.
For the launch, JAXA will perform launch safety control and management (including groundsafety assurance, flight safety assurance, and Y-0 (L-0) countdown operations.) Final go-no go
decision for MHI to carry out the launch will also be determined by JAXA in view of securingsafety.
(3) Developers of Small Secondary Payloads
Each organization develops their respective satellites. The developers will implement
post-separation operations for the respective satellites after being separated from the launchvehicle, including tracking and control and data receiving.

-3-

JAXA

Launch Service Agreement- PLANET-C Development- Launch safety management

Providing launch service- Interface coordination withMHI
- Launch vehicle manufacture- Launch vehicle assembly- Launch preparation operationand launchsmall secondary satellites- Payload interface control

Handover of small secondary satellites

Small Secondary Satellite Developers- Development of respective satellite

-4-

2.3

Launch Organization

The following figure shows the overall organization at the time of launch, and the figures on thenext two pages show MHI’s launch implementation organization and JAXA’s launch safety
management organization.

Director ofKagoshima Space Center(Director for Launch Safety
Control)

Director General for Launch
Assistant to the Director
General for Launch

Assistant to the Director
for Launch Safety Control
Director for Legal Security

Mission Manager

Launch Safety Control
Office

三菱打上げサービス
射場チーム長Flight SafetyGroup

法定保安責任者

Launch Safety
Group

管理グループRange Technology
Development Office

ロケット・設備副長
打上げ運営副長-5-宇宙機器技術部長
二村 幸基

三菱打上げサービス射場チーム長

ミッション・マネージャ

打上げ執行責任者付

打上げ執行責任者
名古屋航空
宇宙システム製作所
技監・技師長前村 孝志

法定保安責任者

管理グループロケット・設備副長

主席プロジェクト
主席プロジェクト
統括
統括
並河 達夫
並河 達夫

打上げ運営副長

MHI Launch Implementation Organization-6-

Director ofKagoshima
Space Center(Director for
Launch Safety
Control)
Norio Sakazume

Kagoshima Space Center
Launch Safety Control OfficeDirector Takahisa Sato
Assistantto theDirector
for Launch Director
Safetyfor Legal
Control
Security

Kagoshima Space Center
Launch Safety Control Office
Flight Safety Group(Flight Safety)
Manager Hirofumi Kawabata

Kagoshima Space Center
Launch Safety Control Office
Launch Safety Group(Security and Safety)
Manager Toru Samejima

Kagoshima Space Cener
Range Technology Development Office(Planning and Management)
Director Takashi Nishida

JAXA launch Safety Management Organization.

-7-

2.4 Launch Vehicle Flight Plan
The H-IIA Launch Vehicle No.17 (H-IIA F17) carrying the Venus Climate Orbiter“PLANET-C” and five small secondary payloads (piggyback payloads) will be launchedvertically from Launch Pad 1 at the Yoshinobu Launch Complex at the Tanegashima Space
Center.
After liftoff, the launch vehicle will shift its pitch plane angle to 93 degrees in azimuth and fly
over the Pacific Ocean according to the scheduled flight path shown in Table-1.
The Solid Rocket Boosters (SRB-As) will be jettisoned at about two minutes and five seconds
after liftoff (hereinafter, time indicates approximate minutes and seconds passed after liftoff)
followed by the jettison of the payload fairing at four minutes and 25 seconds, the first stageengine cutoff at six minutes and 36 seconds, and the first stage jettison at six minutes and 44
seconds.
The second stage engine will be ignited at six minutes and 50 seconds for the first time and cut
off at 11 minutes and 37 seconds. Then the launch vehicle will be injected into the circular orbit
at an altitude of about 300 kilometers with an inclination of 30.0 degrees, then separate thethree small secondary payloads (Negai*”, WASEDA-SAT2, and KSAT) that are packed in the
J-POD (JAXA pocosatellite Orbital Deployer) one by one.
After that (*), the launch vehicle second stage engine will be ignited for a second time at about
23 minutes and 16 seconds, and cut off at about 27 minutes and nine seconds. At about 28
minutes and 12 seconds, PLANET-C will be separated on the Venus transfer orbit.
The H-IIA F17 will continue its coast flight, and it will jettison the PAF900M (Payload Attach
Fitting) at about 36 minutes and 32 seconds and separate the IKAROS at 43 minutes and 27
seconds, and the UNITEC-1 at 48 minutes and 37 seconds.
After completing the above missions, on-orbit technical data will continue to be acquired fromthe launch vehicle second stage propulsion system in order to cope with future controlled
reentry of the second stage.
Table-1 shows the flight plan and Figure-2 shows the scheduled flight trajectory.
* The main mission of the H-IIA F17 is to inject the main payload into Venus transfer orbit;
therefore, the flight plan after separating the J-POD loaded small satellites will be different day
by day. The plan explained here is a case that has the longest coast flight time.

2.5

Major Characteristics of the Launch Vehicle
Table-2 and Figure-3 show the major characteristics and configuration of the launch vehicle.

2.6

Outline of the Main Payload “Venus Climate Orbiter (PLANET-C)”
PLANET-C is a project aiming at observing the Venus atmosphere from the Venus orbit toelucidate mysteries about the Venus atmosphere and to establish planet meteorology as a world
pioneer.
Venus circulates just inside the earth’s revolution orbit, and its average distance from the sun issimilar to that of the Earth. In addition, Venus’s diameter and density are also very close to
those of the Earth, thus it is believed that the two planets were formulated in the similar manner.
However, results of Venus exploration so far indicated that the environments of Venus andEarth are quite different. Venus is covered by the clouds made of concentrated sulfuric acid,and its atmosphere mainly consists of carbon dioxide. Underneath the clouds, the atmospherecirculates to the west at a much faster speed than the Venus’s rotation speed.
In order to clarify the many mysteries about the Venus atmosphere, the PLANET-C project willobserve the planet from the Venus orbit by an explorer with onboard scientific instruments,-8-

including an infrared observation device to acquire three dimensional meteorological data witha high resolution.
Table -3 and Figure 4 respectively show the major characteristics and On-orbit Configurationof the PLANET-C explorer.
2.7 Outline of the Small Secondary Payloads (Piggyback Payloads)
JAXA has a system to provide an easy and quick launch opportunity for small secondary
satellites manufactured by the private sector or universities by using the excessive launchcapability to expand the field of space development utilization in Japan. The system also aims
at contributing to educational opportunities and human resource development using small
satellites.
The small secondary payloads launched by the H-IIA F17 are explained in Table -4 (Outline)
and Figure-5 (Overview and Loading Positions.)
The launch of the small satellites is carried out provided that no adversary impact occurs on themain mission (PLANET-C); therefore, if any sign of such an impact is detected, JAXA may notload the small satellites at its own discretion.
2.8

Securing Launch Safety(1) Safety and Security of Launch Operations
The safety and security of launch-related operations will be secured by taking necessary
actions based on launch-related laws and regulations, guidelines drawn up by the Space
Activities Commission, JAXA standards for payload launch, and regulations and standards
for range safety control regarding the management of hazardous material at the
Tanegashima Space Center.
During launch operations, access will be controlled around the facilities where hazardous
materials are stored and/or handled.
(2) Liaisons with Residents around the Launch Site
For the safety of local residents, JAXA will hold a briefing session with them to announce
the launch plan and ask for their cooperation not to enter access control areas.
(3) Security and Safety Control on the Launch Day(a) Access to areas shown in Figure-6 will be controlled on the launch day of H-IIA Launch
Vehicle No. 17 (H-IIA F17).
(b) Access control on land will be secured by JAXA in cooperation with the Kagoshima
Prefectural Police and Tanegashima Police.
(c) Marine access control will be secured by JAXA, which will monitor the area using
radars and patrol ships in cooperation with the 10th Regional Coast Guard Headquarters
and the Kagoshima Prefectural Government.
(d) For air security and safety over the launch site, JAXA will exchange necessary
information with the Tanegashima Airport Office of the Osaka Aviation Department of
the Ministry of Land, Infrastructure and Transport.
(e) For ships and vessels, JAXA will hoist a yellow flag at two points at the Tanegashima
Space Center on the launch day. They will be replaced with red ones 30 minutes prior
to the liftoff time. A signal flare will be fired two minutes prior to the liftoff. Twoflares will be fired after the launch, and then the red flags will be removed.
(4) Flight Safety of the Launch Vehicle
Flight safety of the launch vehicle after liftoff will be monitored and determined byacquired data from the launch vehicle. Any necessary action will be taken based on this
data.

-9-

2.9

Correspondence Method of Launch Information to Parties Concerned(1) Correspondence regarding Launch Implementation(a) A decision on whether the launch will be held as scheduled or delayed will be finalizedby 3:00 p.m. two days prior to the scheduled launch day, and that decision will be
conveyed to all related organizations listed in a separate document by facsimile.
(b) In the case that the launch is delayed due to adverse weather conditions and/or otherfactors, the postponement and new launch date will be swiftly informed to all relatedorganizations.
(c) JAXA will announce the status of the launch four days and two days prior to the launchday, then six hours, two hours and thirty minutes prior to launch, and again just after
liftoff, to the following parties: the Aeronautical Information Service Center, theKagoshima Airport Office and the Tanegashima Airport Office of the Osaka Aviation
Department, the Air Traffic Control Center, and Air Traffic Control Centers in Tokyo,
Fukuoka, and Naha.
(2) Prior Notice and Launch Information Announcement for Maritime Traffic Safety(a) JAXA will request the Hydrographic and Oceanographic Department of the Japan Coast
Guard to publish a notice to mariners regarding the marine access control areas shownin Figure-6 and the impact areas shown in Figure-7.
(b) For general navigation ships and vessels, JAXA will announce the launch activity, in
addition to the notice for mariners, through radio navigation warnings and shipping
broadcasts by Kyodo News Enterprise (a navigation warning offered by the Japan Coast
Guard.)(c) For shipping vessels, JAXA will announce the launch activity through fishery radio
stations, and the shipping broadcast of Kyodo News Enterprise (a navigation warning
offered by the Japan Coast Guard.)(3) Prior Notice and Launch Information Announcement for Air Traffic Safety
Air traffic safety will be secured through a supplement of the Aviation Information
Publication and the Notice of Airman (NOTAM) issued by the Ministry of Land,
Infrastructure, and Transport (MLIT.) JAXA will place the request well in advanceaccording to Article 99, Section 2, of the Aviation Act and its related regulations, so that the
supplement will be timely issued by the MLIT. The information necessary for issuing the
NOTAM will also be conveyed to the Aeronautical Information Service Center.

3.

Launch Result Report(1) The result of the launch will be swiftly reported to the Ministry of Education, Culture,
Sports, Science and Technology, and the press will also be informed by the Director Generalfor the Launch, Director for Launch Safety Control, or someone equivalent.
(2) JAXA supports press and media coverage activities while paying full attention to maintaintheir safety.

- 10 -JAXA Facilities
NASA Facility

Tanegashima Space Center

Okinawa Tracking and Communication Station

GoddardDownrange Station

Christmas
Downrange Station

Figure-1: Map of Launch Facilities- 11 -

Table-1: Launch Vehicle Flight Plan

Event

Time after liftoff
hr. min. sec.

Altitudekm

Inertial
speed
km/s

1

Liftoff

0

0

0

0.4

2

Solid rocket booster burn out*

1

55

52

1.6

3

Solid rocket booster jettison **

2

5

60

1.6

4

Payload fairing jettison

4

25

147

2.9

5

Main engine cutoff (MECO)

6

36

217

5.5

6

First and second stage separation

6

44

223

5.5

7

Second stage engine first-time ignition (SEIG1)

6

50

226

5.5

8

Second stage engine first-time cutoff (SECO1)

11

37

304

7.7

9

Negai*” (loaded in J-POD) separation

12

39

304

7.7

10 WASEDA-SAT2 (loaded in J-POD) separation

12

49

304

7.7

11 KSAT (loaded in J-POD) separation

12

59

304

7.7

12 Second stage engine second-time ignition (SEIG2)

23

16

299

7.7

13 Second stage engine second-time cutoff (SECO2)

27

9

330

11.7

14 PLANET-C separation

28

12

407

11.7

15 PAF (Payload Attach Fitting) jettison

36

32

2302

10.5

16 IKAROS separation

43

27

4787

9.5

17 UNITEC-1 separation

48

37

6812

8.9

12 Second stage engine second-time ignition (SEIG2)

17

59

302

7.7

13 Second stage engine second-time cutoff (SECO2)

21

51

374

11.6

14 PLANET-C separation

22

55

478

11.5

15 PAF (Payload Attach Fitting) jettison

31

15

2456

10.3

16 IKAROS separation

38

10

4909

9.3

17 UNITEC-1 separation

43

20

6889

8.7

<Longest coast flight case> (See note below)<Shortest coast flight case> (See note below)*) At 2% of the maximum combustion chamber pressure**) Thrust strut cuttingNote) * The main mission of the H-IIA F17 is to inject the main payload into the Venus transfer orbit; therefore, theflight plan after separating the J-POD loaded small satellites will be different day by day. The cases shown above
are example flight cases that have the longest and shortest coast flight time, respectively.

- 12 -

- 13 Note) * The main mission of the H-IIA F17 is to inject the main payload into the Venus transfer orbit; therefore, the flight plan
after separating the J-POD loaded small satellites will be different day by day. The cases shown in the above figure are example
flight cases that have the longest and shortest coast flight time, respectively.

Figure-2: Launch Vehicle Flight Trajectory- 13 -

Table-2 Major: Characteristics of the Launch Vehicle

All Stages
Name

H-IIA Launch Vehicle No. 17

Height (meters)

53

Mass (tons)

289 (Without payloads)

Guidance
MethodInertial Guidance Method
Each Stage
First Stage

Solid Rocket Booster(SRB-A)

Second Stage

Payload Fairing

Height (m)

37

15

11

12

Outside diameter
(m)

4.0

2.5

4.0

4.0

Mass (t)114

153 (For two SRB-As)

20

1.4

101

132 (For two SRB-As)

17－

Thrust (kN)

1,100※

4,525*

137*－

Combustion
duration time (s)

390

120

530

－

Propellant type

Liquidoxygen/hydrogen

Polybutadiene composite
solid propellant

Liquidoxygen/hydrogen－

Propellant supply
systemTurbo pump-

Turbo pump－

Impulse toweight ratio (s)440*283.6*

448*－

Attitude control
methodGimbalsub-engine

Movable nozzle

Gimbalgas jet system－

Propellant
(t)

mass

Major onboard
avionics- Guidance control
equipment- Radar transponder- Telemetrytransmitter- Command destructsystemSolid rocket booster’s thrust is set to the maximum value.

- Guidancecontrolequipment- Telemetrytransmitter* * In vacuum.

- 14 -－

Payload fairing (4S type)

Payload Fairing
12 meters

PLANET-C
Payload separation mechanism
Small secondary payloads
2nd stage liquid hydrogen tank2nd stage liquid oxygen tank

Second Stage
11 meters

2nd stage engine
1st stage liquid oxygen tank

Total
Height53 meters
1st stage liquid hydrogen tank

First
Stage
37 meters

Solid rocket booster

Solid rocket
booster
15 meters

1st stage (main) engine

Figure-3: Configuration of the Launch Vehicle (H2A202 type)- 15 -

Table-3: Major Characteristics of PLANET-C (1/2)
Characteristics/Specifications
Name

Objective

System structure

Venus Climate Orbiter (PLANET-C)
As the world’s first mission to carry out a full-scale study on
atmospheric movement around a planet, PLANET-C is to accurately
observe the meteorological phenomena of Venus hidden underneathclouds from the Venus orbit by using newly developed infraredobservation equipment. Through the observations, it will elucidate
the mechanism of Venus’s atmospheric dynamism (such asplanet-scale high-speed winds) that cannot be explained byconventional meteorology to understand the comprehensive
meteorological phenomena of planets.
1) Mission instruments- 1μm camera (IR1)- 2μm Camera (IR2)- Long wave IR camera (LIR)- Ultraviolet imager (UVI)- Lightening and airglow camera (LAC)- Ultra-stable oscillator (USO)- Digital Electronics (DE)2) Bus- Power system- Communications system- Data processing system- Attitude & orbit control system (AOCS)- Reaction control system (RCS)- Ignition system (IG-BOX)- Structure system- Thermal control system- System wiring harness system (WHS)- 16 -

Table-3: Major Characteristics of PLANET-C (2/2)
Characteristics/Specifications

Design life

Box shape with two wing-type solar array paddles
1040 mm x 1450 mm x 1400 mm
Type:
Venus elliptical orbit
Peri-Venus altitude: 300km
Apo-Venus altitude: about 80,000 km
Orbit period:
30 hours
Orbit inclination angle: 172 degrees
4.5 years after launch

Mass

About 500 kg at the time of liftoff

Power

Generated power: about 500 w in the Venus orbit (at the end of themission)
1μm Camera (IR1)- By capturing infrared emitted from the Venus ground and leaked
to space, the IR1 observes the ground, low stratus and vapor. It
also aims at detecting active volcanism.
Wavelength 0.90, 0.97, 1.01μm; View 12 degrees;
Pixel 1024 x 1024; Detector Si-CSD/CCD
2μm Camera (IR2)- By capturing infrared emitted from the atmosphere that is lower
than low stratus and leaked to space, the IR2 observes distributionof clouds and carbon, and their movement. During its trip fromthe Earth to Venus, it also observes zodiacal light (interplanetary
dust clouds.)
Wavelength 1.65/1.735/2.02/2.26/2.32μm; View 12 degrees;
Pixel 1040 x 1040; Detector PtSi-CSD/CCD
Long wave IR camera (LIR)- By capturing infrared emitted from clouds, the LIR observes thetemperature and distribution of clouds and their changes.
Wavelength 10μm; View 12 degrees;
Pixel 240 x 320; Detector uncooled bolometer
Ultraviolet imager (UVI)- By capturing ultraviolet radiation scattered from clouds, the UVI
observes sulfur dioxide and trace atmospheric contents at thecloud top.
Wavelength 283/365 nm; View 12 degrees;
Pixel 1024 x 1024; Detector Si-CCD
Lightening and airglow camera (LAC)- The LAC observes lightening flashes of lightening discharge andchemical airglow emissions.
Wavelength 542.5/557.7/777.4 nm; View 16 degrees;
Pixel 8 x 8; Detector multi-anode APD
Ultra-stable oscillator (USO)- The USO is onboard for radio occultation measures. It studies thelayer structure of the Venus atmosphere when radio waves
connecting PLANET-C and the ground station pass through theatmosphere.

Shape / Dimension
Scheduled orbit

Mission equipment- 17 -

Figure-4: On-orbit Configuration of PLANET-C- 18 -

Table-4: Outline of the Small Secondary Payloads
Satellite
Developer

Satellite name

JAXA

Small Solar
Power Sail
Demonstrator(IKAROS)- Deployment and extension of the large membrane- Power generation by the thin film solar cells- Verifying acceleration by the solar sail- Acquiring navigation technology by the solar sailBody: Diam. 1.6 m x Height 1.0 m
Membrane (after deployment):
14 m x 14 m
About 315 kg

University
Space
Engineering
Consortium(UNISEC)UNITEC-1- Competition to contend "whose computer for space use willsurvive the longest in deep space" among computers developedby universities for in-orbit verification- Receiving and decoding technology experiments of faint radio
waves from deep space in cooperation with amateur radio
communities.
- Space outreach through the above experiments- Science and engineering mission in deep space (option)

About 39 cm x 39 cm x 42 cm
About 26 kg

WasedaUniversity

WASEDA-SAT-2- QR code image shooting experiment- Providing images to students- Attitude stability by panel deployment

About 10 cm x 10 cm x 10 cm
About 1.2 kg

KSAT- Observation experiments of atmospheric vapor distribution forpredicting localized heavy rain
- Shooting moving images of the Earth through microwave
high-speed communications- Basic communication experiment for super-small positioning
satellites

About 10 cm x 10 cm x 10 cm
About 1.5 kg

Negai*″- Wish upon a shooting star*″ - a satellite to support the future ofchildren- Space verification of the advanced information processing systemusing commercial FPGA

About 10 cm x 10 cm
About 1.0 kg

Kagoshima
University

Soka
University

Mission Outline

Mass/Dimension

Negai☆”WASEDA-SAT2

UNITEC-1

J-POD

KSAT
IKAROS

Figure-5: Overview and Loading Position of the Small Secondary Payloads- 19 -

Land Access Control Area

Marine Access Control Area
Figure-6: Access Control Areas for Launch- 20 -

- 21-

Figure-7: Impact Areas of the Launch Vehicle Jettison