لجنة استخدام الفضاء الخارجي في الأغراض السلمية معلومات مقدمة وفقا لاتفاقية تسجيل الأجسام المطلقة في الفضاء الخارجي مذكرة شفوية مؤرخة 14 آذار/مارس 2003 موجهة إلى الأمين العام من البعثة الدائمة لليابان لدى الأمم المتحدة (فيينا) تهدي البعثة الدائمة لليابان لدى الأمم المتحدة (فيينا) تحياتها إلى الأمين العام للأمم المتحدة، وتتشرف بأن تحيل، وفقا للمادة الرابعة من اتفاقية تسجيل الأجسام المطلقة في الفضاء الخارجي (مرفق قرار الجمعية العامـة 3235 (د-29))، معلومات عن اطلاق الســواتل اليابانيـة التالية: JCSAT-8 و N-STAR c وساتل اختبار ترحيل البيانات (“Kodama”) والساتل المتقدم لرصد الأرض (“Midori-II”) وساتل رصد بيئة الحيتان (“Kantakun”) وساتل LabSat الصغري، والمركبة الفضائية للنظام غير المأهول لاسترجاع التجارب الفضائية (انظر المرفق). المرفق بيانات التسجيل الخاصة بالأجسام الفضائية التي أطلقتها اليابان* ألف- JCSAT-8 باء- N-STAR c جيم- ساتل اختبار ترحيل البيانات (“Kodama”) (drts) دال- الساتل المتقدم لرصد الأرض “Midori-II” هاء- ساتل رصد بيئة الحيتان “Kantakun” واو- ساتل LabSat الصغري زاي- المركبة الفضائية للنظام غير المأهول لاسترجاع التجارب الفضائية ـــــــــــــــــــــــــــــــــــــــــــــــــــــ
Information furnished in conformity with the Convention on Registration of Objects Launched into Outer Space Note verbale dated 14 March 2003 from the Permanent Mission of Japan to the United Nations (Vienna) addressed to the Secretary-General The Permanent Mission of Japan to the United Nations (Vienna) presents its compliments to the Secretary-General of the United Nations and, in accordance with article IV of the Convention on Registration of Objects Launched into Outer Space (General Assembly resolution 3235 (XXIX), annex), has the honour to transmit information concerning the launching of the Japanese satellites JCSAT-8 and N-STAR c, the Data Relay Test Satellite “Kodama”, the Advanced Earth Observation Satellite “Midori-II”, the Whale Ecology Observation Satellite “Kantakun”, Micro LabSat and the Unmanned Space Experiment Recovery System spacecraft (see annex). Annex Registration data for Japanese space launches∗ Name of flight object: JCSAT-8 Designation: 2002-015A Name of launching State: Japan Date and time of launch: 29 March 2002 at 0129 UT Location of launch: Guiana Space Centre, Kourou, French Guiana Basic orbital parameters: (as at 9 May 2002) (a) Nodal period: 1,436 minutes (b) Inclination: 0.012 degrees (c) Apogee: 35,797 kilometres (d) Perigee: 35,778 kilometres General function: Domestic and international telecomunications and domestic broadcasting Launch vehicle: Ariane 44L Launching organization: Arianespace B. N-STAR c Name of flight object N-STAR c Designation: 2002-035B Name of launching State: Japan Date and time of launch: 5 July 2002 at 2321 UT Location of launch: Guiana Space Centre, Kourou, French Guiana Basic orbital parameters: (as at 4 August 2002) (a) Nodal period: 1,436 minutes (b) Inclination: 0.06 degrees (c) Apogee: 35,790 kilometres (d) Perigee: 35,772 kilometres General function: Domestic telecommunications Launch vehicle: Ariane 5 Launching organization: Arianespace C. Data Relay Test Satellite “Kodama” Name of flight object: Data Relay Test Satellite (DRTS) “Kodama” Designation: 2002-042B Name of launching State: Japan Date and time of launch: 10 September 2002 at 0820 UT Location of launch: Tanegashima Space Centre, Kagoshima, Japan Basic orbital parameters: (as at 11 October 2002) (a) Nodal period: 1,436 minutes (b) Inclination: 0.07 degrees (c) Apogee: 35,798.6 kilometres (d) Perigee: 35,774.2 kilometres General function: The main objective of DRTS is the conducting of inter-satellite communication experiments to relay data between the target spacecraft (low-Earth-orbit satellite, space stations and so forth) and ground stations. The satellite is located over 90.75 degrees East. Launch vehicle: H-II A Launch Vehicle F3 (H-IIAF3) Launching organization: National Space Development Agency of Japan Advanced Earth Observation Satellite “Midori-II” Name of flight object: Advanced Earth Observation Satellite II (ADEOS II) “Midori-II” Designation: 2002-056A Name of launching State: Japan Date and time of launch: 14 December 2002 at 0131 UT Location of launch: Tanegashima Space Centre, Kagoshima, Japan Basic orbital parameters: (as at 19 December 2002) (a) Nodal period: 101 minutes (b) Inclination: 98.7 degrees (c) Apogee: 820 kilometres (d) Perigee: 803 kilometres General function: ADEOS II has been developed with the aim of advancing the Earth-observing technologies. ADEOS II is the successor to the first Advanced Earth Observation Satellite, whose mission was to acquire data on the mechanism of global environmental change, including global warming, and on weather phenomena and so forth. Launch vehicle: H-II A Launch Vehicle F4 (H-IIAF4) Launching organization: National Space Development Agency of Japan E. Whale Ecology Observation Satellite “Kantakun” Name of flight object: Whale Ecology Observation Satellite (WEOS) “Kantakun” Designation: 2002-056C Name of launching State: Japan Date and time of launch: 14 December 2002 at 0131 UT Location of launch: Tanegashima Space Centre, Kagoshima, Japan Basic orbital parameters: (as at 17 December 2002) (a) Nodal period: 101 minutes (b) Inclination: 98 degrees (c) Apogee: 812 kilometres (d) Perigee: 774 kilometres General function: The WEOS system consists of a small satellite in a polar orbit, probes attached to whales and a ground station for satellite data reception. The objective of the system is to obtain data on whale ecology and the ocean environment. Launch vehicle: H-II A Launch Vehicle F4 (H-IIAF4) Launching organization: National Space Development Agency of Japan Micro LabSat Name of flight object: Micro LabSat (μ-LabSat) Designation: 2002-056D Name of launching State: Japan Date and time of launch: 14 December 2002 at 0131 UT Location of launch: Tanegashima Space Centre, Kagoshima, Japan Basic orbital parameters: (as at 15 December 2002) (a) Nodal period: 101 minutes (b) Inclination: 98.7 degrees (c) Apogee: 811 kilometres (d) Perigee: 767 kilometres General function: Bus system feasibility for 50 kg-class small satellite; new separator feasibility; and remote inspection technology. Launch vehicle: H-II A Launch Vehicle F4 (H-IIAF4) Launching organization: National Space Development Agency of Japan Unmanned Space Experiment Recovery System spacecraft Name of flight object: Unmanned Space Experiment Recovery System (USERS) spacecraft Designation: 2002-042A Name of launching State: Japan Date and time of launch: 10 September 2002 at 0820 UT Location of launch: Tanegashima Space Centre, Kagoshima, Japan Basic orbital parameters: (as at 8 October 2002) (a) Nodal period: 95 minutes (b) Inclination: 30.4 degrees (c) Apogee: 515 kilometres (d) Perigee: 501 kilometres General function: The mission of the USERS spacecraft is: (a) To establish self-re-entry and return the Unmanned Space Experiment Recovery System; (b) To process high-temperature super-conducting material under microgravity conditions in orbit; (c) To verify commercial parts in a space environment. Launch vehicle: H-II A Launch Vehicle F3 (H-IIAF3) Launching organization: National Space Development Agency of Japan Remark: The re-entry module, part of the USERS spacecraft, is scheduled to separate, re-enter the atmosphere and be guided to a recovery area in the open sea off the Ogasawara islands during the period following May 2003.