Encyclopedia Astronautica
N-2



nasdan2.jpg
Nasda N-2
Nasda N-2 - COSPAR 1981-012
Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle.

LEO Payload: 2,000 kg (4,400 lb) to a 185 km orbit. Payload: 730 kg (1,600 lb) to a GTO in 1985 dollars. Flyaway Unit Cost $: 26.490 million.

Stage Data - N-2

  • Stage 0. 9 x 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. Status: In Production.
  • Stage 1. 1 x 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 2. 1 x 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): 0.0000 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. Status: Out of Production.
  • Stage 3. 1 x 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. Status: Out of Production. 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).

Status: Retired 1987.
Gross mass: 132,690 kg (292,530 lb).
Payload: 2,000 kg (4,400 lb).
Height: 35.00 m (114.00 ft).
Diameter: 2.44 m (8.00 ft).
Thrust: 2,287.50 kN (514,250 lbf).
Apogee: 185 km (114 mi).
First Launch: 1981.02.11.
Last Launch: 1987.02.19.
Number: 8 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • ETS Japanese technology satellite. 7 launches, 1975.09.09 (Kiku 1) to 2006.12.16 (Kiku 8). More...
  • GMS Japanese earth weather satellite. 5 launches, 1977.07.14 (Himawari 1) to 1995.03.18 (Himawari 5). The Geostationary Meteorological Satellite series were spin-stabilized satellites. More...
  • AS 3000 American communications satellite. 25 launches, 1981.11.20 (RCA Satcom 4; RCA Satcom 3R) to 1996.01.14 (Koreasat 2). More...
  • CS-2 Japanese communications satellite. 2 launches, 1983.02.04 (Sakura 2A) to 1983.08.05 (Sakura 2B). Business communications. Launching organization NASDA (National Space Development Agency of Japan). More...
  • Marine Observation Satellite Japanese earth sea satellite. 2 launches, 1987.02.19 (MOS-1) to 1990.02.07 (MOS-1b). The MOS 1A and 1B satellites, also known as Momo 1A and 1B, were Japan's first Earth resources satellites. More...

Associated Engines
  • AJ10-118F Aerojet Nitric acid/UDMH rocket engine. 41.4 kN. Isp=306s. Used on Delta upper stage for Delta 0100, Delta 1000, N-2 boosters. First flight 1972. More...
  • RS-27 Rocketdyne Lox/Kerosene rocket engine. 1023 kN. Out of production. Isp=295s. Consisted of RS2701A/B main engine, and twin LR101-NA-11 verniers. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher; replaced the MB-3. First flight 1972. More...
  • Star 37 Thiokol solid rocket engine. 43.5 kN. Total impulse 161,512 kgf-sec. Motor propellant mass fraction 0.899. Isp=260s. First flight 1963. More...
  • TX-354-3 Thiokol solid rocket engine. 258.9 kN. Used in Scout A; Delta E; H-1-0; Castor 2. License built in Japan for H-1. Isp=262s. First flight 1960. More...

See also
  • Delta The Delta launch vehicle was America's longest-lived, most reliable, and lowest-cost space launch vehicle. Development began in 1955 and it continued in service in the 21st Century despite numerous candidate replacements. More...

Associated Manufacturers and Agencies
  • Mitsubishi Japanese manufacturer of rockets, spacecraft, and rocket engines. Mitsubishi Electric Corp, Japan. More...

Associated Programs
  • BS Medium-scale broadcasting satellites for experimental purposes and communications to Japanese home islands. More...
  • CS Medium-capacity Communications Satellite for Experimental Purposes, a spin stabilized geostationary communications satellite. More...

Associated Launch Sites
  • Tanegashima Japan's main launch site for he larger N and H launch vehicles. In use for sounding rockets from 1967 and orbital launches from 1975. As of 2007 over 140 major launches had been made from the site. More...

Associated Stages
  • Castor 2 Solid propellant rocket stage. Loaded/empty mass 4,424/695 kg. Thrust 258.92 kN. Vacuum specific impulse 262 seconds. More...
  • Delta F Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 5,629/784 kg. Thrust 41.36 kN. Vacuum specific impulse 280 seconds. More...
  • H-1-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 85,800/4,400 kg. Thrust 866.71 kN. Vacuum specific impulse 290 seconds. License built MB-3 ELT Thor More...
  • Star 37E Solid rocket stage. 68.00 kN (15,287 lbf) thrust. Mass 1,123 kg (2,476 lb). More...

N-2 Chronology


1981 February 11 - . 08:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-7(F).
  • Kiku 3 - . Payload: ETS 4. Mass: 640 kg (1,410 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 12295 . COSPAR: 1981-012A. Apogee: 16,237 km (10,089 mi). Perigee: 305 km (189 mi). Inclination: 28.5000 deg. Period: 294.10 min. 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.

1981 August 10 - . 20:03 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-8(F).
  • Himawari 2 - . Payload: GMS 2. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: GMS. Completed Operations Date: 1988-02-01 . USAF Sat Cat: 12677 . COSPAR: 1981-076A. Apogee: 36,034 km (22,390 mi). Perigee: 35,943 km (22,333 mi). Inclination: 12.9000 deg. Period: 1,446.40 min. 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.

1983 February 4 - . 08:37 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-10(F).
  • Sakura 2A - . Payload: CS-2A. Mass: 772 kg (1,701 lb). Nation: Japan. Agency: NASDA. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-2. Completed Operations Date: 1990-12-04 . USAF Sat Cat: 13782 . COSPAR: 1983-006A. Apogee: 36,070 km (22,410 mi). Perigee: 35,994 km (22,365 mi). Inclination: 10.6000 deg. Period: 1,448.70 min. 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.

1983 August 5 - . 20:29 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-11(F).
  • Sakura 2B - . Payload: CS-2B. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-2. Completed Operations Date: 1990-01-01 . USAF Sat Cat: 14248 . COSPAR: 1983-081A. Apogee: 36,210 km (22,490 mi). Perigee: 36,191 km (22,488 mi). Inclination: 5.1000 deg. Period: 1,457.30 min. 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.

1984 January 23 - . 07:58 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-12(F).
  • Yuri 2A - . Payload: BS-2a. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1989-07-01 . USAF Sat Cat: 14659 . COSPAR: 1984-005A. Apogee: 36,191 km (22,488 mi). Perigee: 36,072 km (22,414 mi). Inclination: 4.9000 deg. Period: 1,453.80 min. 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.

1984 August 2 - . 20:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-13(F).
  • Himawari 3 - . Payload: GMS 3. Mass: 303 kg (668 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: GMS. Completed Operations Date: 1995-06-22 . USAF Sat Cat: 15152 . COSPAR: 1984-080A. Apogee: 35,942 km (22,333 mi). Perigee: 35,877 km (22,292 mi). Inclination: 9.8000 deg. Period: 1,442.40 min. 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.

1986 February 12 - . 07:55 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-14(F).
  • Yuri 2B - . Payload: BS-2b. Mass: 677 kg (1,492 lb). Nation: Japan. Agency: NASDA. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1991-10-24 . USAF Sat Cat: 16597 . COSPAR: 1986-016A. Apogee: 36,135 km (22,453 mi). Perigee: 35,996 km (22,366 mi). Inclination: 2.7000 deg. Period: 1,450.40 min. 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.

1987 February 19 - . 01:23 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-16(F).
  • MOS-1 - . Payload: Momo 1. Mass: 745 kg (1,642 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Sea satellite. Spacecraft: Marine Observation Satellite. USAF Sat Cat: 17527 . COSPAR: 1987-018A. Apogee: 909 km (564 mi). Perigee: 907 km (563 mi). Inclination: 99.1000 deg. Period: 103.20 min. Summary: 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..

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