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Launch / Tracking and Control Plan of

Advanced Land Observing Satellite (ALOS) / H-IIA Launch Vehicle No. 8 (H-IIA F8)

November 2005

Japan Aerospace Exploration Agency (JAXA)

(Independent Administrative Agency)

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Table of Contents Page

1. Overview of the Launch / Tracking and Control Plan 1 1.1 Organization in Charge of Launch / Tracking and Control 1 1.2 Person in Charge of Launch / Tracking and Control Operations 1 1.3 Objectives of Launch / Tracking and Control 1 1.4 Payload and Launch Vehicle 1 1.5 Launch Window (Day and Time) 2 1.6 Facilities for Launch / Tracking and Control 2

2. Launch Plan 3

2.1 Launch Site 3 2.2 Launch Organization 4 2.3 Launch Vehicle Flight Plan 5 2.4 Major Characteristics of the Launch Vehicle 5 2.5 Outline of the Advanced Land Observing Satellite (ALOS) 5 2.6 Securing Launch Safety 5 2.7 Correspondence Method of Launch information to Parties Concerned 6

3. Tracking and Control Plan 8

3.1 Tracking and Control Plan of the ALOS 8 3.1.1 Tracking and Control Sites 8 3.1.2 Tracking and Control Organization 8 3.1.3 Tracking and Control Period 8 3.1.4 Tracking and Control Operations 10 3.1.5 ALOS Flight Plan 10 3.1.6 Tracking and Control System 10

4. Launch Result Report 11 [List of Tables]

Table-1: Launch Vehicle Flight Plan 13 Table-2: Major Characteristics of the Launch Vehicle 15 Table-3: Major Characteristics of the ALOS 17 Table-4: Tracking and Control Plan (Stations) of the ALOS 23

[List of Figures]

Figure-1: Map of Launch / Tracking and Control Facilities 12 Figure-2: Launch Vehicle Flight Trajectory 14 Figure-3: Configuration of the Launch Vehicle 16 Figure-4: On-orbit Configuration of the ALOS 20 Figure-5: Access Control Areas for Launch 21 Figure-6: Impact Areas of the Launch Vehicle 22 Figure-7: ALOS Flight Plan 24 Figure-8: ALOS Footprint 25 Figure-9: ALOS Tracking and Control System 26

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1. Overview of the Launch / Tracking and Control Plan

The Japan Aerospace Exploration Agency (hereinafter referred to as “JAXA”), an independent administrative agency, is scheduled to carry out the launch of the Advanced Land Observing Satellite (hereinafter referred to the “ALOS”) using the H-IIA Launch Vehicle No. 8 (hereinafter referred to the “H-IIA F8”) in Japanese Fiscal Year 2005. This document describes the launch plan for the ALOS from the time of the liftoff of the H-IIA F8 through the confirmation of the payload separation from the second stage of the launch vehicle, as well as the tracking and control plan of the initial phase of the ALOS in which its three-axis attitude control stabilization, the initial orbit maneuver to a Sun-synchronous subrecurrent orbit* and functional verification of its onboard equipment will be carried out.

* Sun-synchronous subrecurrent orbit: An orbit in which a satellite orbital plane and the direction to the sun are always constant, and the satellite comes back to one specific spot at about the same time in a constant interval.

1.1 Organization in Charge of Launch / Tracking and Control

Japan Aerospace Exploration Agency (Independent Administrative Agency) President: Keiji Tachikawa Address: 7-44-1 Jindaiji Higashi-machi, Chofu-shi, Tokyo, 182-8522 Japan

1.2 Person in Charge of Launch / Tracking and Control

(1) Director General for Launch Tsukasa Mito, Executive Director

(2) Director General for Tracking and Control Yasushi Horikawa, Executive Director

1.3 Objectives of Launch / Tracking and Control

To launch the ALOS into its scheduled orbit using the H-IIA F8, and carry out tracking and control operations in the initial phase.

1.4 Payload and Launch Vehicle

Launch Vehicle: the H-IIA Launch Vehicle No. 8 (H-IIA F8) (A standard type with a 5-m diameter

fairing and two solid strap-on boosters) =One unit Payload: the Advanced Land Observing Satellite (ALOS) =One unit

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1.5 Launch Window (Day and Time)

Launch Vehicle Type

Scheduled Launch Day

Launch Window

Launch Time

Time of the Launch Vehicle Jettison

(After liftoff) H-IIA Launch Vehicle No. 8 (H-IIA F8)

January 19, 2006

January 20 － February 28, 2006

10:33

to 10:43 a.m.

(JST)

- Solid rocket boosters, solid strap-on boosters, and nozzle closure: about 0 to 1 minute after liftoff.

- Payload fairing: about 9 to 27 minutes after liftoff.

- First stage: about 15 to 33 minutes after liftoff.

Dates and times are Japan Standard Time. 1.6 Facilities for Launch / Tracking and Control

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

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2. Launch Plan 2.1 Launch Site

(1) JAXA Facility (a) Tanegashima Space Center

Oaza-Kukinaga, Minamitane-machi, Kumage-gun, Kagoshima, Japan

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2.2 Launch Organization The following Launch Team led by the Director General for Launch is organized for smooth and accurate operations of launch site activities, the launch itself and payload orbit injection.

Range Director Range Group

Flight Safety Director

Flight Safety Group

Flight Analysis Group

External Affairs Director

External Affairs Group

Guard Director Guard Group

General Affairs Director

General Affairs Group

Facility Group

Assistant to the

Director General

for Launch

Launch Vehicle Director

Quality Assurance Group

Payload Interface

Launch Vehicle Group

Mamoru Endo, H-IIA Project Manage

Ground Support Equipment Group

Tsukasa Mito, Executive Director

of the Office of Space Flight and

Operations

Satellite Director (ALOS) Satellite Group

Public Relations Group

Information CorrespondenceDirector

Information Correspondence Group

Planning Director

Planning Group

Information Network Management Group

Range Safety Director

Range Safety Group

Pad Safety Group

Shoshin Sonoda, Director of the Tanegashima Space Center

Director General for Launch

Deputy Director General

for Launch

Directorfor

Legal Security

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2.3 Launch Vehicle Flight Plan

H-IIA Launch Vehicle No.8 (H-IIA F8) carrying the Advanced Land Observing Satellite (ALOS) will be launched vertically from Launch Pad 1 of the Yoshinobu Launch Complex at the Tanegashima Space Center. After liftoff, the launch vehicle will shift its pitch plane angle to 115 degrees in azimuth and fly over the Pacific Ocean according to the scheduled flight path shown in Table-1. 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 solid strap-on boosters at two minutes and six seconds, the payload fairing jettison at four minutes and 20 seconds, the first stage engine 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 and cut off at 15 minutes and 25 seconds. The ALOS will be separated and injected into a sun-synchronous subrecurrent orbit at 16 minutes and 16 seconds at an altitude of about 700 km with an inclination of 98.2 degrees. Table-1 shows the flight plan and Figure-2 shows the scheduled flight trajectory.

2.4 Major Characteristics of the Launch Vehicle

Table-2 and Figure-3 show the major characteristics and configuration of the launch vehicle.

2.5 Outline of the Advanced Land Observing Satellite (ALOS)

The Advanced Land Observing Satellite (ALOS) aims to collect topographic data to contribute to cartography, regional observation, information gathering from a disaster-stricken area, and recourse surveying by upgrading the land observation technology of the Japan Earth Resources Satellite-1 (JERS-1) and the Advanced Earth Observing Satellite (ADEOS). The ALOS is equipped with three earth observation sensors namely the Remote-sensing Instrument of Stereo Mapping (PRISM) and the Advanced Visible and Near Infrared Radiometer type-2 (AVNIR-2), which were developed by JAXA, and the Phased Array type L-band Synthetic Aperture Radar (PALSAR), which was developed in cooperation with the Japan Resources Observation System Organization of the Ministry of Economy, Trade, and Industry. With these three sensors, the ALOS is expected to carry out high-resolution land observations. Table-3 shows the major characteristics of the ALOS, and Figure-4 shows its configuration.

2.6 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.

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(3) Security and Safety Control on the Launch Day

(a) Access to areas shown in Figure-5 will be controlled on the launch day of H-IIA Launch Vehicle No. 8 (H-IIA F8).

(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. Liaison personnel will be dispatched to the 10th Regional Coast Guard Headquarters Kagoshima Coast Guard to exchange information with the launch site.

(d) For air security and safety over the launch site, JAXA will ask for cooperation from the Kagoshima Airport Office of the Osaka Aviation Department of the Ministry of Land, Infrastructure and Transport, and the Tanegashima Airport Office. A liaison will be dispatched to the Tanegashima Airport Office for closely exchanging information with the launch site.

(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. Two flares 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 by acquired data from the launch vehicle. Any necessary action will be taken based on this data.

2.7 Correspondence Method of Launch Information to Parties Concerned

(1) Correspondence regarding Launch Time/Date Information

(a) The launch day and time will be finalized by 15:00 two days prior to the launch day, and the decision will be conveyed to all related organizations by facsimile.

(b) In the case that the launch is delayed due to adverse weather conditions and/or other factors, the postponement and new launch date will be swiftly informed to all related organizations.

(c) JAXA will announce the status of the launch six hours, two hours and thirty minutes prior to launch, and then again just after liftoff, to the following parties: the New Tokyo Airport (Narita Airport) Office of the Tokyo Aviation Department, the Kagoshima Airport Office and the Tanegashima Airport Office of the Osaka Aviation Department, the Air Traffic Control Center of the Civil Aviation Bureau, 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 Department of the Maritime Safety Agency to publish a notice to mariners regarding the marine access control areas shown in Figure-5 and the impact areas shown in Figure-6.

(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 Maritime Safety Agency).

(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 Maritime Safety Agency).

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(3) Prior Notice and Launch Information Announcement for Air Traffic Safety (a) 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 to the Kagoshima Airport Office of the Osaka Aviation Department of the MLIT according 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 written in the NOTAM will also be conveyed to the New Tokyo Airport (Narita Airport) Office of the Tokyo Aviation Department.

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3. Tracking and Control Plan 3.1 Tracking and Control Plan of the ALOS 3.1.1 Tracking and Control Sites

(1) JAXA Facilities (a) Tracking and Control Building, Tsukuba Space Center

Sengen, Tsukuba-shi, Ibaraki, Japan (b) Masuda Tracking and Communication Station

Masuda, Nakatane-cho, Kumage-gun, Kagoshima, Japan (c) Katsuura Tracking and Communication Station

Haga, Hanatateyama, Katsuura-shi, Chiba, Japan (d) Okinawa Tracking and Communication Station

Kinnabaru, Afuso, Onna-son, Okinawa, Japan (e) Earth Observation Center

Aza-Numanoue, Oaza-Ohashi, Hatoyama-machi, Hiki-gun, Saitama,Japan (f) Kiruna Overseas Mobile Tracking Station

Kiruna, Kingdom of Sweden (g) Perth Overseas Mobile Tracking Station

Perth, Australia (h) Santiago Overseas Mobile Tracking Station

Santiago, Chile (i) Maspalomas Overseas Mobile Tracking Station

Maspalomas, Grand Canary, Canary Islands 3.1.2 Tracking and Control Organization

Tracking and control operations during the ALOS launch and initial phases will be performed by the Tracking and Control Team shown on the next page.

3.1.3 Tracking and Control Period

The tracking and control period for the ALOS launch and initial phases will be about three months after launch. After completing the initial phase, ALOS will move to the regular operation phase that includes about five months of the initial calibration and validation phase. The tracking and control will also be performed during the regular operation phase until the completion of the mission period, which is scheduled to be about three years after launch.

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Tracking and Control Team

Tracking Network GroupTracking Network Director

Planning and Management Group

Planning and Management Director

Information Correspondence Team

Information Correspondence Director

Earth Observation Director Earth Observation Group

Satellite Group Satellite Director

Kenji Tomioka, ALOS Project Manager

Director General for Tracking and Control

Yasushi Horikawa, Executive Director

Acting Director General for

Tracking and Control

Hideshi Kozawa, Associate Executive

Director

Assistant to Director General

Adviser

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3.1.4 Tracking and Control Operations

The ALOS will be launched by the H-IIA F8 to be injected into a sun-synchronous subrecurrent orbit at an altitude of approximately 700 km and with a period of about 99 minutes. Before the establishment of the three-axis attitude, the deployment of the solar array paddle, the Data Relay Satellite Comminucation (DRC) antenna, and the Phased Array type L-band Synthetic Aperture Radar (PALSAR) antenna will be carried out. After injection into orbit, onboard equipment will be checked according to a predetermined check list. Subsequently, the establishment of the three-axis attitude and the initial verification for the bus and mission equipment will follow. Then the ALOS will move to the initial calibration phase and start operating its mission equipment. The tracking and control plan (stations) of the ALOS is shown in Table-4.

3.1.5 ALOS Flight Plan Figure-7 shows the flight plan of the ALOS from the time of the separation from the second stage of the H-IIA F8 through its arrival at its targeted orbit. Figure-8 is the trajectory on-orbit of the ALOS during the same period.

3.1.6 Tracking and Control System

The tracking and control operations system of the ALOS is shown in Figure-9.

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4. Launch Result Report

(1) The result of the launch will be swiftly reported to the Ministry of Education, Culture, Sports, Science and Technology, and a press conference will also be held by the Director General for the Launch.

(2) After the satellite is injected into its orbit, its information will be promptly provided to international organizations such as the Committee on the Peaceful Uses of Outer Space of the United Nations, and the Committee on Space Research, through related government organizations.

(3) JAXA supports press and media coverage activities while maintaining their safety.

JAXA facilities

Okinawa St. 26°30’ Ｎ 127°54’ Ｅ

Masuda St. 30°33’ Ｎ 131°01’ Ｅ

TNSC 30°23’ Ｎ 131°01’ Ｅ

Katsuura St. 35°12’ Ｎ 140°18’ Ｅ

TKSC 36°04’ Ｎ 140°08’ Ｅ

EOC 36°00’ Ｎ 139°21’ Ｅ

KRN1(Kiruna) 67°53’ Ｎ 21°04’ Ｅ

SNT1(Santiago) 33°09’Ｓ 70°40’Ｗ

PRT1(Perth) 31°48’Ｓ 115°53’Ｅ

MSP1(Maspalomas) 27°46’ Ｎ

15°38’ Ｗ

Figure-1: Map of Launch / Tracking and Control Facilities

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TKSC: Tsukuba Space Center TNSC: Tanegashima Space

Center EOC: Earth Observation Center Katsuura St.: Katsuura Tracking

and Communication Station Masuda St.: Masuda Tracking and

Communication Station Okinawa St: Okinawa Tracking

and Communication Station

Table-1 Launch Vehicle Flight Plan

SSB = Solid Strap-on Boosters

SRB-A = Solid Rocket Boosters

Altitude Inertial velocityMin Sec km km/s

1 Liftoff 0 0 0 0.4

2 SSB Ignitions 0 10 0 0.4

3 SSB Burnout 1 8 19 1.0

4 SRB-A Burnout 1 55 55 1.6

5 SRB-A Jettison 2 5 64 1.6

6 SSB Jettison 2 6 65 1.6

7 Payload Fairing Jettison 4 20 165 2.0

8 1st Stage Engine Cutoff 6 36 315 3.6

9 1st and 2nd Stages Separation 6 44 327 3.5

10 2nd Stage Engine 1st Ignition 6 50 336 3.5

11 2nd Stage Engine 1st Cutoff 15 25 697 7.5

12 ALOS Separation 16 16 697 7.5

Events

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Time after liftoff

-10

0

10

20

30

40

50

110 115 120 125 130 135 140 145 150 155 160

経度[東経，度]

地理緯度[北緯，度]

固体ロケットブースタ分離固体補助ロケット分離

衛星フェアリング分離

主エンジン燃焼終了（MECO)

第２段エンジン燃焼終了（SECO)

ALOS分離

Figure-2: Launch Vehicle Flight Trajectory

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Solid Rocket Booster Jettison Solid Strap-on Booster Jettison

Payload Fairing Jettison

Main Engine Cutoff (MECO)

Second Stage Engine

Cutoff (SECO)

ALOS Separation

Latit

ude

[Nor

th la

titud

e, d

egre

es]

Longitude [East longitude, degrees]

Table-2: Major Characteristics of the Launch Vehicle

All Stages

Name H-IIA Launch Vehicle Flight No. 8 (H-IIA F8)

Height (m) 53

Mass (t) 321 (Without payload)

Guidance Method Inertial Guidance Method

Each Stage

First Stage Solid Rocket

Booster (SRB-A)

Second Stage Payload Fairing

Height (m) 37 15 15 11 12

Outside diameter (m) 4.0 2.5 1.0 4.0 5.1

Mass (t) 114 154 (for two)

31 (for two) 20 1.9

Propellant mass (t) 101 132 (for two)

26 (for two) 17

Thrust (KN) 1,100 *１ 4,570 *１ (for two)

1,490*1 (for two)

maximum) 137 *１

Combustion time (s) 390 120 60 530

Propellant type

Liquid oxygen /Liquid hydrogen

Polybutadienecomposite

solid propellant

Polybutadienecomposite

solid propellant

Liquid oxygen /Liquid hydrogen

Propellant supply system Turbo pump － － Turbo pump

Impulse to weight ratio (s) 440 *１ 281 *１ 282*１ 448 *１

Attitude control system

Gimbal Sub-engine

Movable nozzle －

Gimbal Gas jet system

Major onboard electronics devices

- Inertial guidance system

- Telemetry transmitter

－

－ - Guidance

control system,

- Radar transponder,

- Telemetry transmitter,

- Command destruct system

*1: In vacuum. Solid rocket booster’s thrust is set to the maximum value.

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Figure-3: Configuration of the Launch Vehicle

Total Height 53 m

First stage 37 m

Solid rocket booster 15 m

Second stage 11m

Payload Fairing 12 m

ALOS

Payload Fairing (5S type)

Second stage liquid hydrogen tank

Payload separation plane

Second stage liquid oxygen tank

Second stage engine (LE-5B)

First stage liquid oxygen tank

First stage liquid hydrogen tank

Solid rocket booster (SRB-A)

Solid strap-on booster (SSB)

First Stage engine (LE-7A)

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Table-3 Major Characteristics of the ALOS (1/3)

Name Advanced Land Observing Satellite (ALOS) Objectives (1) To carry out technological development necessary for land observation

by a satellite. (2) To contribute to the following areas in cooperation with user

organizations. - Cartography and correction of existing maps in Japan and countries

in the Asian Pacific region. - Regional observation necessary for sustainable development all over

the world. - Prompt information gathering at an area hit by a large-scale disaster

in Japan and overseas. - Recourse surveying in Japan and overseas.

Orbit Type: Sun-synchronous subrecurrent orbit Altitude: 691.65 Km Inclination: 98.16 degrees Period: 98.7 minutes Recurrent period: 46 days Number of recurrence: 14 + 27/46 revolutions / day Orbit per recurrent: 671 revolutions Local time at descending node: 10:30 a.m. +/- 15 minutes Recurrent accuracy: +/- 2.5 km

Configuration / Dimension

A box shaped satellite with one solar array paddle, a Phased Array Type L-band Synthetic Aperture Radar (PALSAR), and a data relay satellite communication antenna Main body: about 6.2 m x 3.5 m x 4.0 m

Solar array paddle: about 3.1 m x 22.2 m PALSAR antenna: about 8.9 m x 3.1 m

Mass 4.00 ton Power generation more than 7,000 W (EOL) Mission life 3 years Attitude control method

Zero-momentum three axis control strapdown system with inertial sensor

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Table-3 Major Characteristics of the ALOS (2/3)

Panchromatic Remote-sensing Instrument for Stereo Mapping (PRISM)

- Sensors developed by: JAXA - Observation band: 1 (Panchromatic) - B/H ratio: 1.0 - Resolution (Nadir) : 2.5 m (about 3.61 µ rad) - Field of View (scanning width): about 2.9 degrees (equivalent to 35 km) 70 km in width for nadir-look - Pointing angle: +/- 1.5 degrees (equivalent to 70 km in width) - Data rate: Less than or equal to 960 Mbps

Advanced Visible and Near Infrared Radiometer Type 2 (AVNIR-2) - Sensors developed by: JAXA - Observation band: 4 - Resolution: 10 m (about 14.28 µ rad) - Field of View (scanning width) : about 5.8 degrees (more than or equal to 70

km) - Pointing angle: +/- less than or equal to 44 degrees - Data rate: 160 Mbps

Phased Array Type L-band Synthetic Aperture Radar (PALSAR) - Sensors developed by: JAXA and Ministry of Economy, Trade and

Industry/JAROS - Frequency: L-band - Method: active phased array - Incidence angle (degrees)

High resolution: 8 to 60 Wide area observation : 18 to 43

- Resolution (m) High resolution: 10 Wide area observation: 100

- Scanning width (km) High resolution: 70 Wide area observation: 350

- Data rate: 240 Mbps / 120 Mbps

Mission Equipment

Technical Engineering Data Acquisition Equipment (TEDA) - Items for measurement: light particles, heavy ions - Data rate 3.712 kbps

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Table-3 Major Characteristics of the ALOS (3/3)

Deployment Monitor (DM)

- Items monitored by DM: PALSAR antenna deployment Solar array paddle deployment Data relay satellite communication antenna deployment ALOS overall movement

- Item monitored by LEM: Launch environment - Number of cameras: 6 cameras (CCD cameras)

Three cameras (maximum) can be operated at the same time Shooting rate: about 7 frames per second (high

speed) about 0.1 frame per second (low speed)

Mission equipment

Laser Reflector (LR) - Method: Prism Array Type - Field of View : Satellite Nadir +/- 60 degrees

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Figu

re-4

: O

n-or

bit

Con

figur

atio

n of

the

ALO

S

Nad

ir

Trav

eling

dire

ction

DR

C A

nten

na

(Dat

a Rela

y Sat

ellite

C

omm

unica

tion A

nten

na)

Solar

Arr

ay P

addl

e

PALS

AR

PRIS

M

AVN

IR-2

Star

Tra

cker

G

PSA

nten

na

30.167

30.333

30.500

30.667

20:00:00 0:00:00 4:00:00 8:00:00 12:00:00

座標系：ＷＧＳ－８４

A

BC

D

E

FG

H

I

130ﾟ50' 131ﾟ00' 131ﾟ10' 131ﾟ20' 131ﾟ30'

30ﾟ10'

30ﾟ20'

30ﾟ30'

30ﾟ40'

Figure-5: Access Control Areas for Launch

Marine Access Control Area

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Land Access Control Area

Space Exhibition Hall

A : 30ﾟ24'04" N, 130ﾟ58'39" EB : 30ﾟ25'40" N, 130ﾟ58'22" EC : 30ﾟ26'48" N, 130ﾟ59'53" ED : 30ﾟ30'00" N, 131ﾟ01'46" EE : 30ﾟ30'00" N, 131ﾟ23'24" EF : 30ﾟ13'48" N, 131ﾟ23'24" EG : 30ﾟ13'48" N, 130ﾟ57'49" EH : 30ﾟ21'57" N, 130ﾟ57'49" EＩ: 30ﾟ22'23" N, 130ﾟ57'39" EE～F: 27.0 km F～G: 42.6 km

East Longitude

Nor

th L

atitu

de

Hirota Port

Yoshinobu Pad 1 Access Control Area

Takesaki Port Observation

deck

Coordinate system: WGS-84

5

10

15

20

25

30

35

125 130 135 140 145

経度[東経，度]

地理緯度[北緯，度]

B473

座標系：ＷＧＳ－８４

　　　固体ロケットブースタ及び 固体補助ロケット落下予想区域 　　 A1 : 29ﾟ04' N, 132ﾟ47' E B1 : 29ﾟ48' N, 133ﾟ09' E C1 : 29ﾟ05' N, 134ﾟ30' E D1 : 28ﾟ15' N, 134ﾟ08' E A１～B１: 88 km B１～C１: 154 km

　　　　衛星フェアリング落下予想区域　

　 A2 : 26ﾟ24' N, 134ﾟ04' E B2 : 26ﾟ22' N, 136ﾟ08' E C2 : 24ﾟ06' N, 136ﾟ06' E D2 : 24ﾟ07' N, 134ﾟ02' E A２～B2: 207 km B2～C2: 250 km

　　 第１段落下予想区域 　　　 A3 : 13ﾟ48' N, 131ﾟ29' E B3 : 13ﾟ05' N, 134ﾟ27' E C3 : 7ﾟ38' N, 133ﾟ07' E D3 : 8ﾟ20' N, 130ﾟ09' E A３～B３: 334 km B３～C３: 619 km

A1 C1

D1

D2

A3

B3

C3

D3

B1

A2

C2

B2

‐22‐

Coordinate system:

WGS-84

Impact area of solid rocket boosters

and solid strap-on boosters

Impact area of payload fairing

Impact area of 1st stage

Latit

ude

[Nor

th la

titud

e, d

egre

es]

Longitude [East longitude, degrees]

Figure-6: Impact Areas of the Launch Vehicle

Tab

le-4

: T

rack

ing

and

Con

trol

Pla

n (S

tatio

ns) o

f the

AL

OS

O

pera

tiona

l pha

se

Laun

ch p

hase

In

itial

pha

se

Gro

und

stat

ions

C

ritic

al p

hase

In

itial

func

tiona

l ver

ifica

tion

phas

e

Reg

ular

Ope

ratio

n ph

ase

(*2)

Tsuk

uba

Trac

king

and

Con

trol B

ldg.

(TA

CC

) ○

○ ○

○

Kat

suur

a 1st

Mob

ile S

tatio

n (K

TU1)

○ ○(

*3)

○(*5

)

Mas

uda

1st M

obile

Sta

tion

(MSD

1)

○(*1

) ○

○(*3

) ○(

*5)

Oki

naw

a 1st

Mob

ile S

tatio

n (O

KN

1)

○ ○

○(*3

) ○(

*5)

Kiru

na 1

st M

obile

Sta

tion

(KR

N1)

○ ○(

*3)

○(*5

)

Perth

1st M

obile

Sta

tion

(PR

T1)

○

○(*3

) ○(

*5)

Sant

iago

1st M

obile

Sta

tion

(SN

T1)

○

○(*3

) ○(

*5)

New GN

Mas

palo

mas

1st M

obile

Sta

tion

(MSP

1)

○

○(*3

) ○(

*5)

Tsuk

uba

Prim

ary

Gro

und

Term

inal

(F

eede

r lin

k st

atio

n) (P

GT)

○(

*3)(

*6)

○

Tracking and Control System

Hat

oyam

a G

roun

d Te

rmin

al (

Feed

er l

ink

stat

ion)

(HG

T)

○(*3

)(*6

) ○

RC

C *

1 ○

R

elat

ed

faci

litie

s EO

C *

2

○ ○(

*4)

○

(*1)

A st

atio

n us

ed a

s a b

acku

p fo

r the

sate

llite

ope

ratio

ns (C

MD

/TLM

) at t

he la

unch

site

bef

ore

laun

ch

(*2)

The

initi

al p

hase

incl

udes

the

initi

al c

alib

ratio

n ph

ase.

(*

3) S

tatio

ns u

sed

for

the

initi

al f

unct

ion

verif

icat

ion

phas

e w

ill b

e de

term

ined

afte

r op

erat

ion

plan

s ar

e ar

rang

ed a

nd c

oord

inat

ed b

y th

e C

onso

lidat

ed S

pace

Tr

acki

ng a

nd D

ata

Acq

uisi

tion

Dep

artm

ent b

ased

on

a re

ques

t fro

m th

e Sa

telli

te G

roup

. The

new

GN

syst

em w

ill b

e op

erat

ed a

s the

mai

n sy

stem

bef

ore

DR

C

chec

kout

, and

the

SN sy

stem

will

serv

e th

is ro

le a

fter D

RC

che

ckou

t. (*

4) A

stat

ion

that

will

be

used

for a

cqui

ring

TED

A d

ata

at a

ll tim

e af

ter s

ix d

ays f

rom

the

laun

ch d

ay.

(*5)

Sta

tions

that

will

be

used

, whe

n ne

cess

ary,

for e

nsur

ing

prec

ise

orbi

t det

erm

inat

ion

and/

or fo

r hou

se k

eepi

ng o

pera

tions

. (*

6) T

he S

SA o

mni

-line

will

be

used

as a

bac

kup

if an

ano

mal

y oc

curs

with

the

USB

line

. *1

RC

C: R

ange

Con

trol C

ente

r (at

Tan

egas

him

a Sp

ace

Cen

ter)

*2

EO

C: E

arth

Obs

erva

tion

Cen

ter (

in H

atoy

ama,

Sai

tam

a, Ja

pan)

‐24‐

　Fi

gure

-7 A

LOS

Flig

ht P

lan

Japanese station first AOC: REV 1

REV 7　DCR pyro igniton 1 to 3

REV 14　DRC deployment

REV 29　PALSAR deployment sequence #1

REV 30　PALSAR deployment sequence #2

Normal Maneuver CMD

Japanese Station

1st AOS

（６）　REV 7 ：　DRC pyro ignition 1 to 3

（７）　REV 14 ：　DRC deployment

　　　　　　　　　　　（DM images recorded to MDR）

（８） REV 27 ：　PALSAR pyro ignition 1 to 3

（９） REV 29 ：　PALSAR deployment sequence #1

（DM images recorded to MDR)

（10） REV 30 ：　PALSAR deployment sequence #2

（11） REV 51 ：　Swith to NM

(1) Launch

REV 0

　（2）　LEM　→　DM switching

　（3）　Satellite separation

　（4）　Paddle deployment

　 　（DM images recorded to MDR）

Mission equipment switched to Sleep Mode

REV 1

　（5）　Paddle sun acquisition start

REV 27　PALSAR pyro ignition

1 to 3

This figure is a schematic drawing that shows major on-orbit events.

Therefore, positions of events in this figure do not accurately correspond

to the points where they will actually take place.

Normal Manuver

(NM)

YawAcquisition

Yawacquisition 　

Paddle Deployment

completed

Paddle

Sun

Tracking

Paddle deployment

start

Launch

Separation

Earth

acquisitoin

Rate Dump

Fi

gure

-8:

AL

OS

traj

ecto

ry o

n-or

bit

ＰＲＴ１

ＭＳＰ１

ＫＲＮ１

ＳＮＴ１

ＯＫＮ１

ＭＳＤ１

ＫＴＵ１

‐25 ‐

Fi

gure

-9:

AL

OS

Tra

ckin

g an

d C

ontr

ol S

yste

m

‐26‐

Kat

suur

a 1s

t M

obile

St.

（ＫＴＵ１）

Mas

uda

1st

Mob

ile S

t. （ＭＳＤ１）

Oki

naw

a 1s

t M

obile

St.

（ＯＫＮ１）

Earth

O

bser

vatio

n C

ente

r (EO

C)

Ove

rsea

s St

atio

ns

Tsuk

uba

Prim

ary

Gro

und

Term

inal

(P

GT)

/ Hat

oyam

a G

roun

d Te

rmin

al

(HG

T) (F

eede

r lin

k st

atio

ns)

Kir

una

1st

Mob

ile S

t. （ＫＲＮ１）

Trac

king

and

Con

trol

Bld

g. T

suku

ba

Spac

e C

ente

r （ＴＡＣＣ）

Rec

eivi

ng P

lan→

←

Rec

eivi

ng r

eque

st

←

MIS

SIO

N D

ATA

TLM

/RN

G

TLM

/RN

G

TLM

/RN

G

TLM

/RN

G

TLM

/RN

G

TLM

/RN

G

TLM

/RN

G

RE

Q/ l

ow m

issi

on d

ata（

TLM、

GU

TS）

CM

D

AN

T-PR

D

CM

D

AN

T-PR

D

CM

D

AN

T-PR

D

CM

D

AN

T-PR

D

OPL

AN

軌道情報

ＣＭＤ：

Com

man

d ＴＬＭ：

Tele

met

ry

ＲＮＧ：

Ran

ging

Dat

a

ＡＬＯＳ

USB

(TLM

,RN

G)

USB

(CM

D,R

NG

)

SSA

(TLM

,RN

G)

KSA

(MIS

SIO

N-D

ATA

)

SSA

(CM

D,R

NG

)

Ka-

BA

ND

(CM

D,R

NG

)

X-B

AN

D(M

ISSI

ON

-DA

TA)

X-B

AN

D(M

ISSI

ON

-DA

TA)

Ka-

BA

ND

(T

LM,R

NG

, M

ISSI

ON

-DA

TA)

CM

D

Perth

1st

M

obile

St.

（ＰＲＴ１）

CM

D

AN

T-PR

D

Sant

iago

1st

M

obile

St.

（ＳＮＴ１）

CM

D

AN

T-PR

D

Mas

palo

mas

1st

M

obile

St.

（ＭＳＰ１）

CM

D

AN

T-PR

D

TLM

/RN

G

ＡＮＴ－ＰＲＤ：

Ant

enna

Pre

dict

ion

ＳＬＲ：

Sate

llite

Las

er R

angi

ng

ＤＲＴＳ

Lase

r R

angi

ng

M

asud

a SL

R＊１

ＲＥＱ

:

O

pera

tion

Req

uest

ＯＰＬＡＮ：

Ope

ratio

n Pl

an

MIS

SIO

N D

ATA：

Mis

sion

Equ

ipm

ent d

ata

＊1)

Su

ppor

ted

by th

e In

tern

atio

nal L

aser

R

angi

ng S

ervi

ce (I

LRS)

in J

apan

and

ove

rsea

s