Encyclopedia Astronautica
N-1 Delta



nasdan1.jpg
Nasda N-1
Nasda N-1 - COSPAR 1975-082
Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle.

LEO Payload: 70,000 kg (154,000 lb) to a 225 km orbit at 51.60 degrees. Failures: 4. Success Rate: 0.00%. First Fail Date: 1969-02-21. Last Fail Date: 1972-11-23. Launch data is: complete in 1985 dollars. Flyaway Unit Cost $: 604.000 million.

Status: Retired 1982.
Gross mass: 131,330 kg (289,530 lb).
Payload: 1,200 kg (2,600 lb).
Height: 34.00 m (111.00 ft).
Diameter: 2.44 m (8.00 ft).
Thrust: 2,287.50 kN (514,250 lbf).
Apogee: 185 km (114 mi).
First Launch: 1975.09.09.
Last Launch: 1982.09.03.
Number: 7 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • ETS Japanese technology satellite. 7 launches, 1975.09.09 (Kiku 1) to 2006.12.16 (Kiku 8). More...
  • JISS Japanese earth ionosphere satellite. 2 launches, 1976.02.29 (ISS 1) to 1978.02.16 (ISS 2). JISS - national name "Ume". Spin-stabilized; Ionospheric Sounder, Radio Noise Receiver, Plasma Measuring Equipment, Ion Mass Spectrometer, and other instruments. More...
  • Ayame Japanese communications technology satellite. 2 launches, 1979.02.06 (Ayame 1) and 1980.02.22 (Ayame 2). Experimental Communications Satellite (ECS). Communications and propagation experiments of satellite-communication systems. More...

Associated Engines
  • 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...
  • 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 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 E Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 6,009/785 kg. Thrust 35.10 kN. Vacuum specific impulse 278 seconds. More...
  • Delta Thor ELT Lox/Kerosene propellant rocket stage. Loaded/empty mass 84,067/4,059 kg. Thrust 1,030.21 kN. Vacuum specific impulse 296 seconds. More...

N-1 Delta Chronology


1975 September 9 - . 05:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-1(F).
  • Kiku 1 - . Payload: ETS 1 (JETS). Mass: 85 kg (187 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 8197 . COSPAR: 1975-082A. Apogee: 1,103 km (685 mi). Perigee: 975 km (605 mi). Inclination: 47.0000 deg. Period: 106.00 min. JETS-1 (Japanese Engineering Test Satellite -1, national name 'Kiku') is intended for preliminary experiments for confirmation of the launching technologies, acquiring the satellite tracking and control technologies, and for extension tests of the extenda ble antennas, measurement of satellite environment, measurement of satellite attitudes, etc. Launch time 0530 GMT.

1976 February 29 - . 03:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-2(F).
  • ISS 1 - . Payload: ISS a. Mass: 139 kg (306 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Ionosphere satellite. Spacecraft: JISS. USAF Sat Cat: 8709 . COSPAR: 1976-019A. Apogee: 1,003 km (623 mi). Perigee: 988 km (613 mi). Inclination: 69.7000 deg. Period: 105.00 min. Ionospheric sounding. Japanese Ionospheric Sounding Satellite (JISS - national name 'Ume') is intended for regular observations by means of radio waves of the global distribution of the critical frequencies of the ionosphere, and for utilization of the results of the observati on for radio wave forecasts and warning necessary for effective operation of short-wave radio-communication. Time of launch 0330UT.

1977 February 23 - . 08:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-3(F).
  • Kiku 2 - . Payload: ETS 2. Mass: 130 kg (280 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. Completed Operations Date: 1990-12-01 . USAF Sat Cat: 9852 . COSPAR: 1977-014A. Apogee: 35,860 km (22,280 mi). Perigee: 35,854 km (22,278 mi). Inclination: 11.9000 deg. Period: 1,439.70 min. Engineering test satellite. Engineering Test Satellite Type II (ETS II), Kiku 2. Launch by N launch vehicle no 3. Geographical longitude of the geostationary orbit: 130 deg E. Preliminary experiments to acquire technologies to launch,track, and control geostationary satellites. P ropagation experiment of millimetre and quasi-millimetre waves. Characteristics: Weight at launch 245 kg. Configuration: cylindrical. Height 191 cm including antenna. Diameter 141 cm. Attitude control: spin stabilization. Expected life at least 6 months. Positioned in geosynchronous orbit over the Pacific Ocean at 130 deg E in 1977-1990 As of 5 September 2001 located at 16.93 deg E drifting at 0.930 deg W per day. As of 2007 Mar 9 located at 85.65W drifting at 0.986W degrees per day.

1978 February 16 - . 04:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-4(F).
  • ISS 2 - . Payload: ISS b. Mass: 140 kg (300 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Ionosphere satellite. Spacecraft: JISS. USAF Sat Cat: 10674 . COSPAR: 1978-018A. Apogee: 1,216 km (755 mi). Perigee: 973 km (604 mi). Inclination: 69.4000 deg. Period: 107.20 min. Ionospheric sounding. Ionosphere Sounding Satellite-b . Launch time 0400 UT. Launch vehicle: N number 4. Spin-stabilized; Ionospheric Sounder, Radio Noise Receiver, Plasma Measuring Equipment, Ion Mass Spectrometer, and so on. The satellite is intended for regular observation of global distribution of critical frequencies of the ionosphere by means of radio waves. Weight about 141 kg. Shape: cylindrical, 3.9m diameter and 0.8m height. Expected life: probability of survival in 1.5 years is more than 70 percent.

1979 February 6 - . 08:46 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-5(F). FAILURE: Third stage collided with ECS a.. Failed Stage: 3.
  • Ayame 1 - . Payload: ECS a; ECS 1. Mass: 260 kg (570 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Communications technology satellite. Spacecraft: Ayame. Completed Operations Date: 1979-02-09 . USAF Sat Cat: 11261 . COSPAR: 1979-009A. Apogee: 37,278 km (23,163 mi). Perigee: 29,407 km (18,272 mi). Inclination: 5.6000 deg. Period: 1,313.10 min. Experimental Communications Satellite. Experimental Communications Satellite (ECS). Launch time 0846 GMT. ECS was injected into the planned transfer orbit. On 9 Feb, however, ECS ceased radio transmissions about 10 seconds after the apogee kick motor was fired. Communicat ions and propagation experiments of satellite-communication systems. Operation and control experiment for geostationary satellites. Mass at launch 260 kg. Configuration - cylindrical. Height 1.9m including antenna. Diameter 1.4m. Spin stabilized. Last known longitude (13 June 1995) 146.23 deg W drifting at 33.817 deg E per day.

1980 February 22 - . 08:35 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-6(F).
  • Ayame 2 - . Payload: ECS b; ECS 2. Mass: 260 kg (570 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Communications technology satellite. Spacecraft: Ayame. Completed Operations Date: 1980-02-24 . USAF Sat Cat: 11715 . COSPAR: 1980-018A. Apogee: 36,839 km (22,890 mi). Perigee: 32,785 km (20,371 mi). Inclination: 1.4000 deg. Period: 1,386.60 min. Summary: Last known longitude (17 November 1988) 146.47 deg W drifting at 12.888 deg E per day..

1982 September 3 - . 05:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-9(F).
  • Kiku 4 - . Payload: ETS 3. Mass: 385 kg (848 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 13492 . COSPAR: 1982-087A. Apogee: 1,006 km (625 mi). Perigee: 988 km (613 mi). Inclination: 44.6000 deg. Period: 105.10 min. Engineering test satellite. Engineering Test Satellite III (ETS-III) launched 0500 GMT 3 Sep 1982 from Osaki launch site, Tanegashima. Launching organization: National Space Development Agency of Japan (NASDA). Verification of three axis attitude control function; verification of so lar array paddle deployment function; verification of active thermal control function; functional test of mission equipment in the space. N launch vehicle flight no 9.

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