Nasda H-1

Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages.

Manufacturer: Mitsubishi. Launches: 9. Success Rate: 100.00%. First Launch Date: 1986-08-12. Last Launch Date: 1992-02-11. Launch data is: complete. LEO Payload: 3,200 kg (7,000 lb). to: 185 km Orbit. Payload: 1,100 kg (2,400 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: AS 3000, CS-3, Debut, EGS, ETS, GMS, JERS, MABES, Marine Observation Satellite, Oscar. Liftoff Thrust: 2,131.800 kN (479,248 lbf). Total Mass: 142,260 kg (313,620 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 42.00 m (137.00 ft). Launch Price $: 90.000 million. in: 1990 price dollars.

4 stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x LE-5 + 1 x UM129A

LEO Payload: 3,200 kg (7,000 lb). to: 185 km Orbit. Payload: 1,100 kg (2,400 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 2,131.800 kN (479,248 lbf). Total Mass: 142,260 kg (313,620 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 42.00 m (137.00 ft).

3 stage version consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x LE-5

Apogee: 1,500 km (900 mi). Liftoff Thrust: 2,130.000 kN (478,840 lbf). Total Mass: 142,000 kg (313,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 42.00 m (137.00 ft).

4 stage version consisting of 6 x Castor 2 + 1 x ELT Thor N + 1 x LE-5 + 1 x UM129A

Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 1,350.000 kN (303,490 lbf). Total Mass: 145,000 kg (319,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 42.00 m (137.00 ft).

• Stage Number: 0. 9 x Stage: Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Isp(sl): 232 sec. Diameter: 0.79 m (2.59 ft). Span: 0.79 m (2.59 ft). Length: 6.04 m (19.81 ft). Propellants: Solid. No Engines: 1. Engine: TX-354-3.

• Stage Number: 1. 1 x Stage: H-1-1. Gross Mass: 85,800 kg (189,100 lb). Empty Mass: 4,400 kg (9,700 lb). Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 270 sec. Isp(sl): 253 sec. Diameter: 2.44 m (8.00 ft). Span: 2.44 m (8.00 ft). Length: 22.00 m (72.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: MB-3-3. Other designations: Extended Length Tank Thor MB-3. License built MB-3 ELT Thor

• Stage Number: 2. 1 x Stage: H-1-2. Gross Mass: 10,600 kg (23,300 lb). Empty Mass: 1,800 kg (3,900 lb). Thrust (vac): 102.900 kN (23,133 lbf). Isp: 450 sec. Burn time: 370 sec. Isp(sl): 0 sec. Diameter: 2.49 m (8.16 ft). Span: 2.49 m (8.16 ft). Length: 10.32 m (33.85 ft). Propellants: Lox/LH2. No Engines: 1. Engine: LE-5. Other designations: LE-5.

• Stage Number: 3. 1 x Stage: H-1-3. Gross Mass: 2,200 kg (4,800 lb). Empty Mass: 360 kg (790 lb). Thrust (vac): 77.400 kN (17,400 lbf). Isp: 291 sec. Burn time: 68 sec. Isp(sl): 220 sec. Diameter: 1.34 m (4.39 ft). Span: 1.34 m (4.39 ft). Length: 2.34 m (7.67 ft). Propellants: Solid. No Engines: 1. Engine: H-1-3. Other designations: UM-129A.

1986 August 12 - 20:45 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: N. Launch Vehicle: H-1. Model: H-1. LV Configuration: H-1 H-15(F).

• EGS Nation: Japan. Payload: EGP. Mass: 685 kg (1,510 lb). Class: Earth. Type: Geodetic. Spacecraft: EGS. Agency: NASDA. Perigee: 1,479 km (919 mi). Apogee: 1,497 km (930 mi). Inclination: 50.00 deg. Period: 115.70 min. COSPAR: 1986-061A. USAF Sat Cat: 16908. Experimental Geophysical Payload; new launch vehicle test flight. EGS (Ajisai). Improvement of the accuracy of domestic geodetic triangulation network. Determination of accurate location of remote islands. Clarification of the relationship between Japanese geodetic system network and those of other areas of the world. L aunch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA.References: 1, 2, 5, 6.

• Oscar 12 Nation: Japan. Program: Oscar. Payload: JAS-1. Mass: 50 kg (110 lb). Class: Communications. Type: Amateur Radio. Spacecraft: Oscar. Agency: JARL. Perigee: 1,479 km (919 mi). Apogee: 1,497 km (930 mi). Inclination: 50.00 deg. Period: 115.70 min. COSPAR: 1986-061B. USAF Sat Cat: 16909. Japanese Amateur Satellite. JAS-1 (Fuji). Amateur satellite communications. Development of amateur satellite technology. Launch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA. Fuji-OSCAR 12 was launched piggyback with a Japanese experimental geodetic satellite Ajisai (EGS). Weight 50 kg. 26-sided polyhedron, 40 x 40 x 47 cm. FO-12 was the first Japanese amateur satellite developed by the Japan Amateur Radio League (English version) with system design and integration performed at NEC. FO-12 was taken out of service November 5, 1989 because of battery failure.References: 1, 2, 5, 6.

• MABES Nation: Japan. Payload: Jindai/LE-5. Class: Technology. Spacecraft: MABES. Agency: NASDA. Perigee: 1,483 km (921 mi). Apogee: 1,604 km (996 mi). Inclination: 50.00 deg. Period: 117.00 min. COSPAR: 1986-061C. USAF Sat Cat: 16910. MABES (Jindai). Experiment on the levitation of the magnetic bearing flywheel under zero-g condition. References: 1, 2, 5, 6.

• Kiku 5 Nation: Japan. Payload: ETS 5. Mass: 550 kg (1,210 lb). Class: Technology. Spacecraft: ETS. Agency: NASDA. Perigee: 36,029 km (22,387 mi). Apogee: 36,072 km (22,414 mi). Inclination: 7.90 deg. Period: 1,449.60 min. COSPAR: 1987-070A. USAF Sat Cat: 18316. Completed Operations Date: 1997-09-10. Stationed at 150 deg E. ETS-V (Kiku-5). Establishment of basic technology for bus systems needed for 3-axis stabilized geostationary satellites. Accumulation of key technologies required for high performance in the next generation of applications satellites; Experiment of mobile satellite communications for the control of aircrafts over the Pacific Ocean, and for the communication, navigational aid, search and rescue of ships. H-I (3-stage) launch vehicle. Launching organization NASDA. Launch time 0920 GMT. Positioned in geosynchronous orbit at 150 deg E in 1987-1997 As of 5 September 2001 located at 92.55 deg W drifting at 3.394 deg W per day. As of 2007 Mar 10 located at 49.74W drifting at 3.380W degrees per day.References: 1, 2, 5, 6.

• Sakura 3A Nation: Japan. Program: CS. Payload: CS-3A. Mass: 1,100 kg (2,400 lb). Class: Communications. Spacecraft: CS-3. Agency: NASDA/TC. Perigee: 36,376 km (22,602 mi). Apogee: 36,415 km (22,627 mi). Inclination: 4.90 deg. Period: 1,467.30 min. COSPAR: 1988-012A. USAF Sat Cat: 18877. Completed Operations Date: 1996-09-28. Stationed at 132 deg E. CS-3A (Sakura 3-A). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications. To develop technologies for communications satellites. Launch vehicle H18F. Launchin g organization NASDA. Launch time 1005 GMT. Positioned in geosynchronous orbit at 132 deg E in 1988-1996 As of 2 September 2001 located at 85.60 deg E drifting at 7.699 deg W per day. As of 2007 Mar 10 located at 71.73E drifting at 7.700W degrees per day.References: 1, 2, 5, 6.

• Sakura 3B Nation: Japan. Program: CS. Payload: CS-3B. Mass: 1,100 kg (2,400 lb). Class: Communications. Spacecraft: CS-3. Agency: NASDA/TC. Perigee: 36,071 km (22,413 mi). Apogee: 36,093 km (22,427 mi). Inclination: 4.00 deg. Period: 1,451.20 min. COSPAR: 1988-086A. USAF Sat Cat: 19508. Completed Operations Date: 1997-11-10. Telephone communications; 136 deg E. CS-3B (Sakura 3-B). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications; to develop technologies for communications satellites. Launch vehicle H-I (H19F). La unching organization NASDA. Launch time 0959 GMT. Positioned in geosynchronous orbit at 149 deg E in 1988; 136 deg E in 1988-1997; 154 deg E in 1997 As of 28 August 2001 located at 128.96 deg W drifting at 3.783 deg W per day. As of 2007 Mar 10 located at 177.82E drifting at 3.765W degrees per day.References: 1, 2, 5, 6.

• Himawari 4 Nation: Japan. Payload: GMS 4. Mass: 725 kg (1,598 lb). Class: Earth. Type: Weather. Spacecraft: GMS. Agency: NASDA. Perigee: 36,410 km (22,620 mi). Apogee: 36,807 km (22,870 mi). Inclination: 6.20 deg. Period: 1,478.30 min. COSPAR: 1989-070A. USAF Sat Cat: 20217. Completed Operations Date: 2000-02-24. Stationed at 140 deg E. GMS-4 (Himawari-4). Improvement of meteorological observation. Development of meteorological satellite technology. Launch vehicle H-I (H20F). Launching organization NASDA. Launch time 1911 GMT. Positioned in geosynchronous orbit at 160 deg E in 1989; 140 deg E in 1989-1995; 120 deg E in 1995-1999 As of 4 September 2001 located at 126.83 deg E drifting at 10.301 deg W per day. As of 2007 Mar 9 located at 71.28W drifting at 10.305W degrees per day.References: 1, 2, 5, 6.

• MOS-1b Nation: Japan. Payload: Momo 1B. Mass: 740 kg (1,630 lb). Class: Earth. Type: Seasat. Spacecraft: Marine Observation Satellite. Agency: NASDA. Perigee: 908 km (564 mi). Apogee: 909 km (564 mi). Inclination: 99.10 deg. Period: 103.20 min. COSPAR: 1990-013A. USAF Sat Cat: 20478. Marine observation. Continuation of Earth observation functions of MOS-1; establishment of common technology necessary for Earth-observation satellites. Launching organization NASDA. Name MOS-1b 'Momo-1b'. Launch time 0133 UT. References: 1, 2, 5, 6.

• Debut Nation: Japan. Payload: Orizuru. Mass: 50 kg (110 lb). Class: Technology. Spacecraft: Debut. Agency: NASDA. Perigee: 911 km (566 mi). Apogee: 1,743 km (1,083 mi). Inclination: 99.00 deg. Period: 112.20 min. COSPAR: 1990-013B. USAF Sat Cat: 20479. Boom, umbrella test. DEBUT 'Orizuru'. Experiment of extending and contracting boom; experiment of expanding and contracting aerodynamic brake. Launching organization NASDA. Launch time 0133 UT. References: 1, 2, 5, 6.

• Oscar 20 Nation: Japan. Program: Oscar. Payload: JAS 1b. Mass: 50 kg (110 lb). Class: Communications. Type: Amateur Radio. Spacecraft: Oscar. Agency: JARL. Perigee: 912 km (566 mi). Apogee: 1,745 km (1,084 mi). Inclination: 99.00 deg. Period: 112.20 min. COSPAR: 1990-013C. USAF Sat Cat: 20480. JAS-1b 'Fuji-2'. Continuation of amateurradio services of JAS-1; extension of amateur radio communications area; advancement of amateur radio technology. Launching organization NASDA. Launch time 0133 UT. References: 1, 2, 5, 6.

• Yuri 3A Nation: Japan. Program: BS. Payload: BS-3a. Mass: 1,115 kg (2,458 lb). Class: Communications. Spacecraft: AS 3000. Agency: NASDA/TC. Manufacturer: Lockheed Martin. Perigee: 36,157 km (22,466 mi). Apogee: 36,245 km (22,521 mi). Inclination: 3.50 deg. Period: 1,457.30 min. COSPAR: 1990-077A. USAF Sat Cat: 20771. Completed Operations Date: 1998-04-20. Japanese DBS; 110 deg E. Continuation of broadcasting services by BS-2; accommodations to increasing and diversifying demands for broadcasting; establishment of common technology necessary for broadcasting satellite. Launching organization NASDA. Launch time 0905 GMT. BS-3a 'Yuri -3a'. Positioned in geosynchronous orbit at 110 deg E in 1990-1998 As of 2 September 2001 located at 84.62 deg E drifting at 5.278 deg W per day. As of 2007 Mar 10 located at 83.70W drifting at 5.275W degrees per day.References: 1, 2, 5, 6.

• Yuri 3B Nation: Japan. Program: BS. Payload: BS-3b. Mass: 1,115 kg (2,458 lb). Class: Communications. Spacecraft: AS 3000. Agency: NASDA/TC. Manufacturer: Lockheed Martin. Perigee: 36,171 km (22,475 mi). Apogee: 36,244 km (22,520 mi). Inclination: 3.20 deg. Period: 1,457.70 min. COSPAR: 1991-060A. USAF Sat Cat: 21668. Completed Operations Date: 1999-04-05. TV; 110 deg E. Positioned in geosynchronous orbit at 110 deg E in 1991-1999 As of 3 September 2001 located at 91.59 deg E drifting at 5.350 deg W per day. As of 2007 Mar 9 located at 152.69E drifting at 5.334W degrees per day. References: 1, 2, 5, 6.

• JERS-1 Nation: Japan. Payload: ERS-1. Mass: 1,340 kg (2,950 lb). Class: Earth. Type: Landsat. Spacecraft: JERS. Agency: NASDA. Perigee: 567 km (352 mi). Apogee: 568 km (352 mi). Inclination: 97.70 deg. Period: 96.00 min. COSPAR: 1992-007A. USAF Sat Cat: 21867. Completed Operations Date: 1998-10-12. Decay Date: 2001-12-03. Japanese Research Satellite-1. JERS-1 (FUYO-1). To verify functions and performance of optical sensors and a Synthetic Aperture Radar and to establish an integrated system for observing the Earth's resources; to perform observations and measurements for land survey, agriculture, forest ry, fishery, environmental preservation, disaster prevention and coastal surveillance. Launch time 0150 GMT. Launching organization NASDA. The Japanese Fuyo-1 (ERS-1) satellite failed on Oct 12, 1998 after six years of operation.References: 1, 2, 5, 6.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al. ISBN: 0710618107. The most comprehensive source of information for current space projects. Too expensive for human beings and most libraries. More at amazon.com...