Nasda N-1

Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor N + 1 x LE-3 + 1 x Star 37N

Manufacturer: Mitsubishi. Launches: 7. Failures: 1. Success Rate: 85.71%. First Launch Date: 1975-09-09. Last Launch Date: 1982-09-03. Launch data is: complete. LEO Payload: 1,200 kg (2,600 lb). to: 185 km Orbit. Payload: 360 kg (790 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: Ayame, ETS, JISS. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 131,330 kg (289,530 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 34.00 m (111.00 ft). Flyaway Unit Cost $: 23.010 million. in: 1985 unit dollars.

• 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 E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 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: AJ10-118E.

1975 September 9 - 05:30 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: N. Launch Vehicle: N. Model: N-1. LV Configuration: N-1 N-1(F).

• Kiku 1 Nation: Japan. Payload: ETS 1 (JETS). Mass: 85 kg (187 lb). Class: Technology. Spacecraft: ETS. Agency: NASDA. Perigee: 975 km (605 mi). Apogee: 1,103 km (685 mi). Inclination: 47.00 deg. Period: 106.00 min. COSPAR: 1975-082A. USAF Sat Cat: 8197. 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.References: 1, 2, 5, 6.

• ISS 1 Nation: Japan. Payload: ISS a. Mass: 139 kg (306 lb). Class: Earth. Type: Ionosphere. Spacecraft: JISS. Agency: NASDA. Perigee: 988 km (613 mi). Apogee: 1,003 km (623 mi). Inclination: 69.70 deg. Period: 105.00 min. COSPAR: 1976-019A. USAF Sat Cat: 8709. 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.References: 1, 2, 5, 6.

• Kiku 2 Nation: Japan. Payload: ETS 2. Mass: 130 kg (280 lb). Class: Technology. Spacecraft: ETS. Agency: NASDA. Perigee: 35,854 km (22,278 mi). Apogee: 35,860 km (22,280 mi). Inclination: 11.90 deg. Period: 1,439.70 min. COSPAR: 1977-014A. USAF Sat Cat: 9852. Completed Operations Date: 1990-12-01. 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.References: 1, 2, 5, 6.

• ISS 2 Nation: Japan. Payload: ISS b. Mass: 140 kg (300 lb). Class: Earth. Type: Ionosphere. Spacecraft: JISS. Agency: NASDA. Perigee: 973 km (604 mi). Apogee: 1,216 km (755 mi). Inclination: 69.40 deg. Period: 107.20 min. COSPAR: 1978-018A. USAF Sat Cat: 10674. 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.References: 1, 2, 5, 6.

• Ayame 1 Nation: Japan. Payload: ECS a; ECS 1. Mass: 260 kg (570 lb). Class: Technology. Type: Comsat. Spacecraft: Ayame. Agency: NASDA. Perigee: 29,407 km (18,272 mi). Apogee: 37,278 km (23,163 mi). Inclination: 5.60 deg. Period: 1,313.10 min. COSPAR: 1979-009A. USAF Sat Cat: 11261. Completed Operations Date: 1979-02-09. 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.References: 1, 2, 5, 6.

• Ayame 2 Nation: Japan. Payload: ECS b; ECS 2. Mass: 260 kg (570 lb). Class: Technology. Type: Comsat. Spacecraft: Ayame. Agency: NASDA. Perigee: 32,785 km (20,371 mi). Apogee: 36,839 km (22,890 mi). Inclination: 1.40 deg. Period: 1,386.60 min. COSPAR: 1980-018A. USAF Sat Cat: 11715. Completed Operations Date: 1980-02-24. Last known longitude (17 November 1988) 146.47 deg W drifting at 12.888 deg E per day. References: 1, 2, 5, 6.

• Kiku 4 Nation: Japan. Payload: ETS 3. Mass: 385 kg (848 lb). Class: Technology. Spacecraft: ETS. Agency: NASDA. Perigee: 988 km (613 mi). Apogee: 1,006 km (625 mi). Inclination: 44.60 deg. Period: 105.10 min. COSPAR: 1982-087A. USAF Sat Cat: 13492. 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.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.

• Gatland, Kenneth, Missiles and Rockets, Macmillan, New York, 1975. ISBN: 0713735058. Covers rocketry of all nations. More at amazon.com...