Nasda N-2

Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x AJ10-118FJ + 1 x Star 37E.

Manufacturer: Mitsubishi. Launches: 8. Success Rate: 100.00%. First Launch Date: 1981-02-11. Last Launch Date: 1987-02-19. Launch data is: complete. LEO Payload: 2,000 kg (4,400 lb). to: 185 km Orbit. Payload: 730 kg (1,600 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: AS 3000, CS-2, ETS, GMS, Marine Observation Satellite. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 132,690 kg (292,530 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft). Flyaway Unit Cost $: 26.490 million. in: 1985 unit dollars.

4 stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x AJ10-118FJ + 1 x Star 37E.

LEO Payload: 2,000 kg (4,400 lb). to: 185 km Orbit. Payload: 730 kg (1,600 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 132,690 kg (292,530 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

3 stage version consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x AJ10-118FJ

Apogee: 1,000 km (600 mi). Liftoff Thrust: 2,290.000 kN (514,810 lbf). Total Mass: 133,000 kg (293,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 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: Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Isp(sl): 262 sec. Diameter: 2.44 m (8.00 ft). Span: 2.44 m (8.00 ft). Length: 22.40 m (73.40 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RS-27. Other designations: Extended Length Tank Thor. Status: Out of production.

• Stage Number: 2. 1 x Stage: Delta F. Gross Mass: 5,629 kg (12,409 lb). Empty Mass: 784 kg (1,728 lb). Thrust (vac): 41.364 kN (9,299 lbf). Isp: 280 sec. Burn time: 335 sec. Isp(sl): 0 sec. Diameter: 1.40 m (4.50 ft). Span: 1.40 m (4.50 ft). Length: 6.28 m (20.60 ft). Propellants: Nitric acid/UDMH. No Engines: 1. Engine: AJ10-118F.

• Stage Number: 3. 1 x Stage: Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Isp(sl): 220 sec. Diameter: 0.66 m (2.16 ft). Span: 0.66 m (2.16 ft). Length: 0.84 m (2.75 ft). Propellants: Solid. No Engines: 1. Engine: Star 37. Burner II was a launch vehicle upper stage developed by Boeing for the Air Force Space Systems Division. It was the first solid-fuel upper stage with full control and guidance capability developed for general space applications. Burner II was designed for use with the Thor booster, but was readily adapted for use on the complete range of standard launch vehicles. Its general assignment was to place small- and medium size payloads into orbit. The Burner II motor, guidance system and reaction control system were integrated to provide attitude stability and precise control of flight rate and burnout velocity for orbital injection and earth-escape missions. Boeing had delivered 8 flight vehicles under its original contract. Under terms of a follow-on contract, it built 6 additional flight models. Four Thor-Burner II combinations were launched successfully from Vandenberg Air Force Base, California. The third launch placed 2 unclassified satellites in Earth orbit. A SECOR satellite, built for the U.S. Army Corps of Engineers by the Cubic Corporation, and an Aurora satellite, developed by Rice University for the Office of Naval Research, were placed in circular orbits 3,300 km above the Earth. As integration contractor for the Air Force Space Experiment Support Program (SESP) Office, Boeing designed, built and tested the injection stage, or "payload dispenser," which carried the 2 satellites on top of a standard Burner II stage and placed them in precise orbits. The satellites were mounted on opposite sides of the injection stage, which housed a640 kgf thrust, solid-propellant rocket motor. The Burner II was used as an upper stage by NASA for deep space probes. Prime Contractor: The Boeing Company. Major Subcontractors Thiokol Chemical Corporation (solid rocket motor); Honeywell Inc. (pre-programmed inertial guidance system); Walter Kidde Co. (reaction control system).

1981 February 11 - 08:30 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: N. Launch Vehicle: N-2. Model: N-2. LV Configuration: N-2 N-7(F).

• Kiku 3 Nation: Japan. Payload: ETS 4. Mass: 640 kg (1,410 lb). Class: Technology. Spacecraft: ETS. Agency: NASDA. Perigee: 305 km (189 mi). Apogee: 16,237 km (10,089 mi). Inclination: 28.50 deg. Period: 294.10 min. COSPAR: 1981-012A. USAF Sat Cat: 12295. Kiku 3 (ETS-IV). Launching organization NASDA. Acquisition of the technology to handle a large-scale heavy satellite and test of the functions of on-board equipment and devices, as well as confirmation of the launching capacity of the N-II launch vehicle. Also tested ion thruster.References: 1, 2, 5, 6.

• Himawari 2 Nation: Japan. Payload: GMS 2. Mass: 670 kg (1,470 lb). Class: Earth. Type: Weather. Spacecraft: GMS. Agency: NASDA. Perigee: 35,943 km (22,333 mi). Apogee: 36,034 km (22,390 mi). Inclination: 12.90 deg. Period: 1,446.40 min. COSPAR: 1981-076A. USAF Sat Cat: 12677. Completed Operations Date: 1988-02-01. Geostationary meteorological satellite. N launch vehicle flight number 8 (N-II launch vehicle). Launch time 2003 UT. Launching organization: National Space Development Agency of Japan (NASDA). Geostationary longitude 140 deg E. Function: 1) Observation of meteorological phenomena by the visible and infra-red spin scan radiometer. 2) Collection of weather data from various stations. 3) Distribution of weather data to earth stations. 4) Monitoring of solar particles. Positioned in geosynchronous orbit at 160 deg E in 1981; 140 deg E in 1981-1984; 145 deg E in 1984-1985; 120 deg E in 1985-1988 As of 31 August 2001 located at 33.93 deg E drifting at 2.598 deg W per day. As of 2007 Mar 9 located at 153.66W drifting at 2.594W degrees per day.References: 1, 2, 5, 6.

• Sakura 2A Nation: Japan. Program: CS. Payload: CS-2A. Mass: 772 kg (1,701 lb). Class: Communications. Spacecraft: CS-2. Agency: NASDA. Perigee: 35,994 km (22,365 mi). Apogee: 36,070 km (22,410 mi). Inclination: 10.60 deg. Period: 1,448.70 min. COSPAR: 1983-006A. USAF Sat Cat: 13782. Completed Operations Date: 1990-12-04. Business communications. Launch time 0837 GMT. Launching organization NASDA (National Space Development Agency of Japan). N launch vehicle No. 10(F) (N-II launch vehicle). Osaki launch site, NASDA Tanegashima Space Center, Kagoshima, Japan. Geostationary position 132 deg E. Estab lishment of domestic satellite telecommunications network mainly for natural disaster, emergency and for remote islands using submillimetre wavelength and microwavelength signals. Development of the technology of communications satellite. Positioned in geosynchronous orbit at 132 deg E in 1983-1988; 128 deg E in 1988-1990 As of 30 August 2001 located at 140.81 deg E drifting at 3.111 deg W per day. As of 2007 Mar 10 located at 31.02W drifting at 3.113W degrees per day.References: 1, 2, 5, 6.

• Sakura 2B Nation: Japan. Program: CS. Payload: CS-2B. Mass: 670 kg (1,470 lb). Class: Communications. Spacecraft: CS-2. Agency: NASDA. Perigee: 36,191 km (22,488 mi). Apogee: 36,210 km (22,490 mi). Inclination: 5.10 deg. Period: 1,457.30 min. COSPAR: 1983-081A. USAF Sat Cat: 14248. Completed Operations Date: 1990-01-01. CS-2b (Sakura 2b). Launch time 2029 GMT. Launching organization NASDA (National Space Development Agency of Japan). N launch vehicle flight no. 11 (N-II launch vehicle). Domestic satellite communications; development of communications satellite technolog y. Positioned in geosynchronous orbit at 136 deg E in 1983-1989; 128 deg E in 1989-1990 As of 4 September 2001 located at 154.41 deg E drifting at 5.251 deg W per day. As of 2007 Mar 10 located at 13.72E drifting at 5.257W degrees per day.References: 1, 2, 5, 6.

• Yuri 2A Nation: Japan. Program: BS. Payload: BS-2a. Mass: 670 kg (1,470 lb). Class: Communications. Spacecraft: AS 3000. Agency: NASDA. Manufacturer: Lockheed Martin. Perigee: 36,072 km (22,414 mi). Apogee: 36,191 km (22,488 mi). Inclination: 4.90 deg. Period: 1,453.80 min. COSPAR: 1984-005A. USAF Sat Cat: 14659. Completed Operations Date: 1989-07-01. TV. BS-2a (Yuri-2a). Domestic satellite broadcasting; development of broadcasting satellite technology. Launch 0758 GMT. N launch vehicle flight no 12. Launching organization NASDA. Positioned in geosynchronous orbit at 110 deg E in 1984-1985; 108 deg E in 1985-1987; 110 deg E in 1987-1988 As of 28 August 2001 located at 69.57 deg E drifting at 4.403 deg W per day. As of 2007 Mar 10 located at 153.52W drifting at 4.395W degrees per day.References: 1, 2, 5, 6.

• Himawari 3 Nation: Japan. Payload: GMS 3. Mass: 303 kg (668 lb). Class: Earth. Type: Weather. Spacecraft: GMS. Agency: NASDA. Perigee: 35,877 km (22,292 mi). Apogee: 35,942 km (22,333 mi). Inclination: 9.80 deg. Period: 1,442.40 min. COSPAR: 1984-080A. USAF Sat Cat: 15152. Completed Operations Date: 1995-06-22. Stationed at 140 deg E; also studied alpha particles, electrons. GMS-3 (Himawari-3). Launch 2030 GMT. Improvement of meteorological observation. Development of meteorological satellite technology. N Launch vehicle flight no 13. Launching organization NASDA. Positioned in geosynchronous orbit at 140 deg E in 1984-1989; 120 deg E in 1989-1995 As of 28 August 2001 located at 146.92 deg E drifting at 1.558 deg W per day. As of 2007 Mar 11 located at 168.90W drifting at 1.566W degrees per day.References: 1, 2, 5, 6.

• Yuri 2B Nation: Japan. Program: BS. Payload: BS-2b. Mass: 677 kg (1,492 lb). Class: Communications. Spacecraft: AS 3000. Agency: NASDA. Manufacturer: Lockheed Martin. Perigee: 35,996 km (22,366 mi). Apogee: 36,135 km (22,453 mi). Inclination: 2.70 deg. Period: 1,450.40 min. COSPAR: 1986-016A. USAF Sat Cat: 16597. Completed Operations Date: 1991-10-24. Stationed at 117 deg E. BS-2b (Yuri-2b). Domestic satellite broadcasting; development of broadcasting satellite technology. Launching organization NASDA. N launch vehicle flight no 14. Launch time 0755 GMT. Positioned in geosynchronous orbit at 110 deg E in 1986-1991 As of 5 September 2001 located at 13.60 deg W drifting at 3.524 deg W per day. As of 2007 Mar 11 located at 77.04E drifting at 3.551W degrees per day.References: 1, 2, 5, 6.

• MOS-1 Nation: Japan. Payload: Momo 1. Mass: 745 kg (1,642 lb). Class: Earth. Type: Seasat. Spacecraft: Marine Observation Satellite. Agency: NASDA. Perigee: 907 km (563 mi). Apogee: 909 km (564 mi). Inclination: 99.10 deg. Period: 103.20 min. COSPAR: 1987-018A. USAF Sat Cat: 17527. Ocean remote sensing. MOS-1 (Momo-1). Observation of marine phenomena such as sea color and temperature. Establishment of common technology necessary for Earth observation satellites. Launching organization NASDA. Launch time 0123 GMT. 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...