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 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 Scheduled Launch Launch Time of the Launch Vehicle Type Launch Day Window Time Jettison (After liftoff) - Solid rocket boosters, solid strap-on boosters, and H-IIA Launch January 19, January 20 － 10:33 nozzle closure: about 0 to 1 Vehicle No. 8 2006 February 28, 2006 to minute after liftoff. (H-IIA F8) 10:43 a.m. - Payload fairing: about 9 to (JST) 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) Oaza-Kukinaga, Minamitane-machi, Kumage-gun, Kagoshima, Japan

- 3 - 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.

Launch Vehicle Launch Vehicle Group Director Ground Support Equipment Group

Payload Interface

Mamoru Endo, Quality Assurance Group H-IIA Project Manage

Satellite Director (ALOS) Satellite Group

Director General Deputy for Launch Director General for Assistant Director Range Director Range Group Launch to the for Director Legal General Security for Flight Safety Director Flight Analysis Group Launch Tsukasa Mito, Flight Safety Group Executive Director of the Office of Space Flight and Shoshin Sonoda, Range Safety Director Range Safety Group Operations Director of the Tanegashima Pad Safety Group

Space Center Guard Director Guard Group

Planning Planning Group Director

Information Network Management Group

Information Information Correspondence Correspondence Group Director Public Relations Group

General Affairs General Affairs Group Director

Facility Group

External Affairs External Affairs Group Director

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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).

- 6 - (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.

- 7 - 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, 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) 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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Satellite Director Satellite Group

Kenji Tomioka, ALOS Project Manager

Earth Observation Director Earth Observation Group

Director General for Tracking Network Director Tracking Network Group Tracking and Control Assistant Adviser to Director General

Yasushi Horikawa, Executive Director

Acting Director Planning and Planning and General for Management Director Management Group Tracking and Control

Hideshi Kozawa, Associate Executive Director Information Information Correspondence Correspondence Director Team

Tracking and Control Team

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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.

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JAXA facilities

EOC 36°00’ Ｎ 139°21’ Ｅ

TKSC 36°04’ Ｎ 140°08’ Ｅ

TKSC: Tsukuba Space Center Katsuura St. TNSC: Tanegashima Space 35°12’ Ｎ Center 140°18’ Ｅ EOC: Earth Observation Center Katsuura St.: Katsuura Tracking Masuda St. TNSC and Communication Station 30°33’ Ｎ 30°23’ Ｎ Masuda St.: Masuda Tracking and 131°01’ Ｅ Communication Station 131°01’ Ｅ Okinawa St: Okinawa Tracking Okinawa St. and Communication Station 26°30’ Ｎ 127°54’ Ｅ

SNT1(Santiago)

33°09’Ｓ 70°40’Ｗ

MSP1(Maspalomas) KRN1(Kiruna) 27°46’ Ｎ 67°53’ Ｎ 15°38’ Ｗ 21°04’ Ｅ PRT1(Perth)

31°48’Ｓ 115°53’Ｅ

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

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Table-1 Launch Vehicle Flight Plan

Events Time after liftoff Altitude Inertial velocity Min 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

SSB = Solid Strap-on Boosters SRB-A = Solid Rocket Boosters

‐13‐ 50

40

Solid固体ロケットブースタ分離 Rocket Booster Jettison Solid固体補助ロケット分離 Strap-on Booster Jettison

30 衛星フェアリング分離Payload Fairing Jettison

主エンジン燃焼終了Main Engine Cutoff (MECO) （MECO)

20 地理緯度[北緯，度] Latitude [North latitude, degrees] latitude, [North Latitude

10

第２段エンジン燃焼終了Second Stage Engine （SECO) Cutoff (SECO)

ALOS分離ALOS Separation 0

-10 110 115 120 125 130 135 140 145 150 155 160 経度[東経，度] Longitude [East longitude, degrees]

Figure-2: Launch Vehicle Flight Trajectory

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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 Solid Rocket Payload First Stage Booster Second Stage Fairing (SRB-A)

Height (m) 37 15 15 11 12

Outside diameter (m) 4.0 2.5 1.0 4.0 5.1 154 31 Mass (t) 114 20 1.9 (for two) (for two) 132 26 Propellant mass (t) 101 17 (for two) (for two) 1,490*1 4,570 *１ Thrust (KN) 1,100 *１ (for two) 137 *１ (for two) maximum) Combustion time (s) 390 120 60 530 Liquid oxygen Polybutadiene Polybutadiene Liquid oxygen Propellant type /Liquid hydrogen composite composite /Liquid hydrogen solid solid propellant propellant Propellant supply Turbo pump － － Turbo pump system Impulse to weight 440 *１ 281 *１ 282*１ 448 *１ ratio (s) Attitude control Gimbal Movable Gimbal system Sub-engine nozzle － Gas jet system

Major onboard - Inertial - Guidance electronics devices guidance － － control system system, - Telemetry - Radar transmitter transponder, - Telemetry transmitter, - Command destruct system *1: In vacuum. Solid rocket booster’s thrust is set to the maximum value.

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Payload Fairing (5S type)

ALOS Payload Fairing 12 m Payload separation plane

Second stage liquid hydrogen tank

Second Second stage liquid oxygen tank stage 11m Second stage engine (LE-5B)

Total First stage liquid oxygen tank Height 53 m

First stage First stage liquid hydrogen tank 37 m

Solid rocket booster (SRB-A)

Solid rocket booster Solid strap-on booster (SSB) 15 m

First Stage engine (LE-7A)

Figure-3: Configuration of the Launch Vehicle

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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 / A box shaped satellite with one solar array paddle, a Phased Array Type Dimension 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 Zero-momentum three axis control strapdown system with inertial sensor method

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

- 18 - 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 Mission equipment same time Shooting rate: about 7 frames per second (high speed) about 0.1 frame per second (low speed) Laser Reflector (LR) - Method: Prism Array Type - Field of View : Satellite Nadir +/- 60 degrees

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DRC Antenna (Data Relay Satellite Communication Antenna)

Star Tracker GPS Antenna ‐

20 Solar Array Paddle ‐

PALSAR

Nadir AVNIR-2 Traveling direction

PRISM

Figure-4: On-orbit Configuration of the ALOS Hirota Port

Yoshinobu Pad 1 Access Control Area

Space Exhibition Hall Observation deck Takesaki Port

Land Access Control Area

30.66730ﾟ40' A : 30ﾟ24'04" N, 130ﾟ58'39" E B : 30ﾟ25'40" N, 130ﾟ58'22" E C : 30ﾟ26'48" N, 130ﾟ59'53" E D : 30ﾟ30'00" N, 131ﾟ01'46" E E : 30ﾟ30'00" N, 131ﾟ23'24" E F : 30ﾟ13'48" N, 131ﾟ23'24" E G : 30ﾟ13'48" N, 130ﾟ57'49" E E 30.50030ﾟ30' H : 30ﾟ21'57" N, 130ﾟ57'49" E D Ｉ: 30ﾟ22'23" N, 130ﾟ57'39" E E～F: 27.0 km F～G: 42.6 km C B

A I North Latitude Latitude North H 30.33330ﾟ20'

G F

Coordinate座標系：ＷＧＳ－８４ system: WGS-84 30.16730ﾟ10' 20:00:00130ﾟ50' 0:00:00131ﾟ00' 131ﾟ10' 4:00:00131ﾟ20' 8:00:00131ﾟ30' 12:00:00

East Longitude

Marine Access Control Area

Figure-5: Access Control Areas for Launch -21- 35

Coordinate system: 座標系：ＷＧＳ－８４ WGS-84

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

A2 B2

25

D2 C2

Impact 衛星フェアリング落下予想区域 area of payload fairing

A2 : 26ﾟ24' N, 134ﾟ04' E B2 : 26ﾟ22' N, 136ﾟ08' E 20 C2 : 24ﾟ06' N, 136ﾟ06' E D2 : 24ﾟ07' N, 134ﾟ02' E

地理緯度[北緯，度] A２～B2: 207 km B2～C2: 250 km Latitude [North latitude, degrees] degrees] latitude, [North Latitude

15

A3

B3

Impact 第１段落下予想区域 area of 1st stage

A3 : 13ﾟ48' N, 131ﾟ29' E 10 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 D3

C3

B473

5 125 130 135 140 145 Longitude経度[東経，度] [East longitude, degrees]

Figure-6: Impact Areas of the Launch Vehicle

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Table-4: Tracking and Control Plan (Stations) of the ALOS

Operational phase Launch phase Initial phase Regular Operation phase Ground stations Critical phase Initial functional verification (*2) phase Tsukuba Tracking and Control Bldg. (TACC) ○ ○ ○ ○ Katsuura 1st Mobile Station (KTU1) ○ ○(*3) ○(*5) Tracking andControlSystem Masuda 1st Mobile Station (MSD1) ○(*1) ○ ○(*3) ○(*5) st New GN Okinawa 1 Mobile Station (OKN1) ○ ○ ○(*3) ○(*5) Kiruna 1st Mobile Station (KRN1) ○ ○(*3) ○(*5) Perth 1st Mobile Station (PRT1) ○ ○(*3) ○(*5) Santiago 1st Mobile Station (SNT1) ○ ○(*3) ○(*5) Maspalomas 1st Mobile Station (MSP1) ○ ○(*3) ○(*5)

Tsukuba Primary Ground Terminal ○(*3)(*6) ○ (Feeder link station) (PGT) Hatoyama Ground Terminal (Feeder link ○(*3)(*6) ○ station) (HGT) Related RCC *1 ○ facilities EOC *2 ○ ○(*4) ○

(*1) A station used as a backup for the satellite operations (CMD/TLM) at the launch site before launch (*2) The initial phase includes the initial calibration phase. (*3) Stations used for the initial function verification phase will be determined after operation plans are arranged and coordinated by the Consolidated Space Tracking and Data Acquisition Department based on a request from the Satellite Group. The new GN system will be operated as the main system before DRC checkout, and the SN system will serve this role after DRC checkout. (*4) A station that will be used for acquiring TEDA data at all time after six days from the launch day. (*5) Stations that will be used, when necessary, for ensuring precise orbit determination and/or for house keeping operations. (*6) The SSA omni-line will be used as a backup if an anomaly occurs with the USB line. *1 RCC: Range Control Center (at Tanegashima Space Center) *2 EOC: Earth Observation Center (in Hatoyama, Saitama, Japan) ents. correspond REV 27 PALSAR pyro ignition pyro 27 PALSAR REV 1 to 3 REV 14 DRCREV deployment REV 7 DCR pyro igniton 1 to 3 1 to igniton pyro 7 DCR REV REV 29 PALSAR deployment sequence #1 sequence deployment 29 PALSAR REV #2 sequence deployment 30 PALSAR REV Normal Maneuver CMD This figure is a schematic drawing that shows major on-orbit ev Therefore, positions of events in this figure do not accurately to the points where they will actually take place. Paddle Sun Tracking Launch Japanese Station 1st AOS

Separation Yaw Acquisition Rate Dump Yaw acquisition Earth acquisitoin Normal Manuver (NM) Paddle deployment start Paddle Deployment completed Figure-7 ALOS Flight Plan

(1) Launch deployment ： DRC 14 （７） REV （DMimages recorded toMDR） （６） REV7 ： DRC pyroignition 1 to3 3 to 1 ignition pyro ： PALSAR 27 REV （８） #2 sequence deployment ： PALSAR 30 REV （10） （９） REV 29 ： PALSAR deployment sequence #1 sequence deployment ： PALSAR 29 REV （９） （DM imagesrecorded toMDR) （11） REV 51 ： Swith to NM to ： Swith 51 REV （11） REV 1 start acquisition sun （5） Paddle Japanese station first AOC: REV 1 REV 0 switching （2） LEM → DM separation （3） Satellite deployment （4） Paddle （DM images recorded toMDR） Mission equipment switched to Sleep Mode

‐24‐ ＫＲＮ１

ＫＴＵ１

ＭＳＰ１ ＭＳＤ１

ＯＫＮ１

‐ 25 ‐

ＳＮＴ１ ＰＲＴ１

Figure-8: ALOS trajectory on-orbit

ＡＬＯＳ SSA(CMD,RNG) ＤＲＴＳ

SSA(TLM,RNG)

KSA(MISSION-DATA) USB(CMD,RNG) Laser Ranging Ka-BAND(CMD,RNG) X-BAND(MISSION-DATA)

X-BAND(MISSION-DATA) Ka-BAND

(TLM,RNG, USB(TLM,RNG) MISSION-DATA)

Tsukuba Primary Earth Masuda Maspalomas 1st Santiago 1st Perth 1st Kiruna 1st Katsuura 1st Masuda 1st Okinawa 1st Overseas Ground Terminal Observation SLR＊１ (PGT)/ Hatoyama Mobile St. Mobile St. Mobile St. Mobile St. Mobile St. Mobile St. Mobile St. Center (EOC) Stations Ground Terminal ‐ （ＭＳＰ１） （ＳＮＴ１） （ＰＲＴ１） （ＫＲＮ１） （ＫＴＵ１） （ＭＳＤ１） （ＯＫＮ１） (HGT) (Feeder link 26 OPLAN stations)

‐ CMD CMD CMD CMD CMD CMD CMD 軌道情報

ANT-PRD ANT-PRD ANT-PRD ANT-PRD ANT-PRD ANT-PRD ANT-PRD TLM/RNG TLM/RNG Receiving Plan→ CMD TLM/RNG TLM/RNG ←Receiving request TLM/RNG REQ/ low mission data（TLM、GUTS） ←MISSION DATA TLM/RNG TLM/RNG TLM/RNG

Tracking and Control Bldg. Tsukuba Space Center （ＴＡＣＣ）

＊1) ＣＭＤ： Command ＡＮＴ－ＰＲＤ：Antenna Prediction ＲＥＱ: Operation Request Supported by the International Laser ＴＬＭ：Telemetry Ranging Service (ILRS) in Japan and overseas ＳＬＲ：Satellite Laser Ranging ＯＰＬＡＮ：Operation Plan ＲＮＧ：Ranging Data

MISSION DATA：Mission Equipment data

Figure-9: ALOS Tracking and Control System