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The Japanese N-Launch Vehicle The Space Congress® Proceedings 1981 (18th) The Year of the Shuttle Apr 1st, 8:00 AM The Japanese N-Launch Vehicle Yukihiko Takenaka Director, Launch Vehicle Design Group, National Space Development Agency of Japan Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Takenaka, Yukihiko, "The Japanese N-Launch Vehicle" (1981). The Space Congress® Proceedings. 6. https://commons.erau.edu/space-congress-proceedings/proceedings-1981-18th/session-6/6 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. JAPANESE N LAUNCH VEHICLE Yukihiko Takenaka Director, Launch Vehicle Design Group National Space Development Agency of Japan ABSTRACT vehicle became operational in 1975 when it successfully put an 85 kg Engineering Test Satellite into a planned The N series rocket is a three stage, Thor-Delta type orbit accurately in its first flight. Since then the N-I satellite launcher developed and operated under the rocket, Japan's first liquid booster, has launched six management of the National Space Development Agency satellites in total; with five successful flights and one of Japan. This liquid propellant booster was completed malfunction connected with the mission failure. with a great deal of the support from the United States. A significant launch took place in 1977 when NASDA The first generation of the N, N-I vehicle capable successfully put a 1 30 kg Engineering Test Satellite into of placing a 130kg pay load into geostationary orbit, geostationary orbit for the first time in Japan by using has launched six satellites in total since 1975 with one the N-I rocket. Figure 1 shows a typical lift-off scene of malfunction connected with the mission failure. An the N-I rocket at the Tanegashima launch site. upgraded version of the N-I, called N-II launch vehicle, was successfully launched this past February in its first The N-II launch vehicle is an upgraded version of flight. At present this rocket is the heaviest satellite the N-I vehicle. This project started in 1976 and the launcher in Japan, capable of placing about 350 kg pay- first flight was successfully conducted this past February load into geostationary orbit. to put a 640 kg Engineering Test Satellite into geosynchro­ nous transfer orbit. Figure 2 shows the lift-off scene of This paper describes overall features of both N-I this first N-II launch. and N-II launch vehicles including configuration, sub­ systems and capability. Typical launch preparation Japan's heaviest satellite launcher at the present activities such as the factory checkout and launch site time, the N-II vehicle will replace the N-I soon and is operations are also introduced. scheduled to launch various applications satellites over the next several years. 1. Introduction The mission summary of the N program is shown in Table 1. Over the past ten years the National Space Develop­ ment Agency of Japan (NASDA) has been engaged in the Development and operation of a satellite launcher 2. Main Characteristics of the N Series called N rocket. NASDA is now responsible for its use Rocket and continued improvement work. Cutaway views of N-I and N-II vehicles are shown The N series rocket is a three stage booster capable in Fig. 3. Figure 4 shows configurations of both vehicles. of launching medium size applications satellites. The Also, main characteristics are listed in Table 2. N launch vehicle program, from the basic N, called N-I vehicle, through the current N, called N-II vehicle, has The N-I rocket is a three-stage, radio-guided vehicle been supported by the United States through govern­ with overall length of 32.6 m, maximum diameter of ment level agreements. Hardware and technology of 2.4 rn and a lift-off weight of 90 tons. The first stage the NASA Thor-Delta have been transferred and applied consists of a MB-3 engine, liquid prepellant tank and to both N-I and N-II vehicles. three Castor-II solid strap-on boosters (SOB): 1968 Thor-Delta components but license-produced in Japan. The N-I rocket project started in 1970 and this launch The second stage propulsion system uses a regeneratively 6-21 Table 1 N Program Mission Summary Launched Orbit Flight Satellite Launch Weight Parameters Launch Status Number Name Date (kg) (km/km/deg.) Vehicle 1 ETS-I 9/9/75 83 1100/980/47 N-l Engineering test satellite 2 ISS 2/29/76 139 1010/990/70 N-l Ionosphere sounding satellite 3 ETS-I I 2/23/77 130 geostationary N-l Engineering test satellite orbit 4 ISS-b 2/16/78 141 1220/980/70 N-l Ionosphere sounding satellite iv-i t-Apei linemen uuiiimuiiiuduuna satellite was placed into geo­ synchronous transfer orbit, but failed to reach geostationary orbit due to spacecraft/vehicle collision. 6 ECS-b o/oo/on ion N-l Experimental communications satellite was placed into geo­ synchronous transfer orbit. Mission failure due to ABM malfunction. 7 ETS-IV 2/11/81 640 35800/225/28.5 N-l I Engineering test satellite Scheduled Orbit Flight Satellite Launch Approximate Parameters Launch Mission Number Name Year Weight (kg) (km/km/deg.) Vehicle 8 GMS-2 1981 340 geostationary N-ll Meteorological satellite orbit 9 ETS-I 1 1 1982 385 1000/1000/45 N-l Engineering test satellite 10 CS-2a 1983 350 geostationary N-ll Domestic communications orbit satellite 11 CS-2b 1983 350 geostationary N-ll Domestic communications orbit satellite 12 BS-2a 1984 350 geostationary N-ll Domestic broadcasting orbit satellite 13 GMS-3 1984 340 geostationary M-ll Meteorological satellite orbit 14 MOS-1 1985 750 910/910/99 N-ll Marine observation satellite sunsynchronous orbit 15 BS«2b 10S5 350 geosynchronous N-ll Domestic broadcasting satellite orbit 16 AIV1ES 1986 350 geosynchronous N-ll Navigation satellite orbit 6-22 Table 2 Main Characteristics of N-I and N-ll Vehicles Vehicle ^^-— —— _____ IM-I N-ll Size Overall length (m) 32.6 35.4 Diameter (m) 2.44 2.44 Lift-off weight (approx. ton) 90 135 First stage Propetlant (oxidizer/fuel) LOX/RJ-1 LOX/RJ-1 Average thrust (ton, sea level) 77 77 Specific impulse (sec, sea level) 249 249 Total/propel la nt weight (ton) 70/66 86/81 Strap-On- Propel lant (oxidizer/fuel) Solid Solid Booster Average thrust (ton, sea level) 23.7 x 3 23.7 x 9 Total /propel lant weight (ton) 4.5/3.75 x 3 4.5/3.75 x 9 Second Propellant (oxidizer/fuel) N 2 0 4 /A-50 N 2 04 /A-50 stage Average thrust (ton, vacuum) 5.4 4.4 Specific impulse (sec, vacuum) 285 315 Total/propellant weight (ton) 5.8/4.7 6.75/5.80 Third stage Propellant (oxidizer/fuel) Solid Solid Average thrust (ton, vacuum) 4.0 (TE-364-14) 6.8 (TE-364-4) Propellant weight (ton) 0.56 1.05 Fairing Diameter (m) 1.65 2.44 Max. diameter of satellite accommodated (m) 1.44 Approx. 2 Guidance system Radio guidance Delta Inertia! Guidance System cooled LR-3 engine and a liquid propellant tank, which Figure 5 shows major improvements applied to the were developed in Japan. An off-loaded TE-364-3 solid N-II vehicle as compared to the N-I vehicle. The second motor of the Delta vehicle is used as the third stage. stage propulsion system of both rockets is compared With this configuration, the N-I vehicle is capable of in Fig. 6. placing a 130kg payload into geostationary orbit from The performance capability of the N-II vehicle is the Tanegashima launch site located at about 30° N greatly increased as a result of the improvements des­ latitude. cribed above. The typical payload capability and orbit The N-II vehicle, an upgraded version of the N-I accuracy are shown in Table 3. The two-stage circular vehicle, is 35.4m long and 2.4m in diameter with a orbit capability of the N-II vehicle is shown in Fig. 7. lift-off weight of 135 tons. This new launch vehicle has the capability of placing a 350 kg payload into geo­ 3. Brief Description of the Current N Vehicle stationary orbit. The first stage uses a longer propellant The first stage MB-3 engine uses a bipropellant tank with the same MB-3 engine and nine Castor-II strap- combination of liquid oxygen and kerosene on boosters. (RJ-1), de­ veloping an average thrust of 77 tons at sea level. It The second stage propulsion system (SSPS), AJ10- burns for 268 sec, assisted by 6 SOBs during the first 118FJ, has been improved from the basic Delta second 39 sec, then successively by 3 SOBs. The vehicle control stage by an U.S. company. The engine has a restart is carried out by the engine gimballing system and two capability with an ablative cooling system. small vernier engines. The first stage extended long tank is made of aluminum alloy and has a monocoque A larger solid motor, TE-364-4, is a Delta component structure with machined isogrid lattices. applied to the N-II third stage. Also, the Delta Inertial Guidance System (DIGS) is employed for guidance and A schematic description of the first stage is shown control of the vehicle. in Fig. 8. Figure 9 shows the MB-3 engine during ac- 6-23 Table 3 Typical Peformance Capability and 3 Sigma Orbit Accuracy foriM-l and N-ll Vehicles ^^— —^ N-l Vehicle N-H Vehicle Geosynchronous Flight mode 3 stage parking-transfer 3 stage parking-transfer transfer orbit Apogee altitude (krn) 35 ,786 ± 2,800 35,786 ± 1,000 Perigee altitude (km) 190 ± 18 225 ± 8 Inclination (deg.) 30.5 ± 0.7 28.5 ± 0.7 Payload weight (kg) 319 670 Sun synchronous Flight mode 2 stage Hohmann orbit -(circular) Altitude (km) 910 ± 19 Inclination (dij.) 99 + 0.05 Payload (kg) 750 ceptance firing test conducted, at the NASDA test facility.
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