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S-210
Credit - JAXA
Sounding rocket. Country: Japan. Status: Active.

Series of Japanese single-stage sounding rockets designed for low-cost observations of the ionosphere.

Manufacturer: Mitsubishi. Launches: 204. Failures: 4. Success Rate: 98.04%. First Launch Date: 1963-08-10. Last Launch Date: 2007-01-16. Launch data is: continuing. Apogee: 50 km (31 mi). Total Length: 2.80 m (9.10 ft). Version:

S-A. Status: Retired 1963.

Single stage vehicle.

Launches: 3. First Launch Date: 1963-08-10. Last Launch Date: 1963-08-10. Apogee: 50 km (31 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 100 kg (220 lb). Core Diameter: 0.16 m (0.52 ft). Total Length: 2.80 m (9.10 ft).

  • Stage1: 1 x S-A-1. Gross Mass: 100 kg (220 lb). Motor: 1 x S-A. Length: 2.80 m (9.10 ft). Diameter: 0.16 m (0.52 ft). Propellants: Solid.
Version:

SA-II. Status: Retired 1968.

Single stage vehicle.

Manufacturer: STA. Launches: 1. First Launch Date: 1968-09-17. Last Launch Date: 1968-09-17. Apogee: 20 km (12 mi). Liftoff Thrust: 0 N ( lbf). Core Diameter: 0.10 m (0.32 ft).

Version:

S-B. Status: Retired 1971.

Single stage vehicle.

Launches: 12. First Launch Date: 1964-07-17. Last Launch Date: 1971-09-11. Apogee: 75 km (46 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 100 kg (220 lb). Core Diameter: 0.16 m (0.52 ft). Total Length: 2.80 m (9.10 ft).

  • Stage1: 1 x S-B-1. Gross Mass: 100 kg (220 lb). Motor: 1 x S-B. Length: 2.80 m (9.10 ft). Diameter: 0.16 m (0.52 ft). Propellants: Solid.
Version:

S-C. Status: Retired 1969.

Single stage vehicle.

Launches: 3. First Launch Date: 1969-02-07. Last Launch Date: 1969-02-08. Apogee: 85 km (52 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 100 kg (220 lb). Core Diameter: 0.17 m (0.55 ft). Total Length: 2.90 m (9.50 ft).

  • Stage1: 1 x S-C-1. Gross Mass: 100 kg (220 lb). Motor: 1 x S-C. Length: 2.80 m (9.10 ft). Diameter: 0.16 m (0.52 ft). Propellants: Solid.
Version:

ST. Test vehicle. Status: Retired 1965.

Single stage vehicle.

Manufacturer: STA. Launches: 1. First Launch Date: 1965-11-16. Last Launch Date: 1965-11-16. Apogee: 20 km (12 mi). Liftoff Thrust: 0 N ( lbf). Core Diameter: 0.10 m (0.32 ft).

  • Stage1: 1 x ST-1. Motor: 1 x ST. Length: 1.00 m (3.20 ft). Diameter: 0.10 m (0.32 ft). Propellants: Solid.
Version:

JCR. Status: Retired 1974.

Single stage vehicle.

Manufacturer: NASDA. Launches: 10. First Launch Date: 1969-09-15. Last Launch Date: 1974-02-01. Apogee: 200 km (120 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,300 kg (5,000 lb). Core Diameter: 0.50 m (1.64 ft). Total Length: 7.00 m (22.90 ft).

  • Stage1: 1 x JCR-1. Gross Mass: 700 kg (1,540 lb). Motor: 1 x JCR. Length: 7.00 m (22.90 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.
Version:

HM-16. Status: Retired 1965.

Single stage vehicle.

Manufacturer: STA. Launches: 2. First Launch Date: 1965-06-17. Last Launch Date: 1965-06-18. Apogee: 20 km (12 mi). Liftoff Thrust: 10.000 kN (2,248 lbf). Core Diameter: 0.10 m (0.32 ft). Total Length: 3.60 m (11.80 ft).

  • Stage1: 1 x HM-16-1. Gross Mass: 100 kg (220 lb). Motor: 1 x HM-16. Length: 1.00 m (3.20 ft). Diameter: 0.17 m (0.54 ft). Propellants: Solid.
Version:

NAL-16. Test vehicle. Status: Retired 1969.

Single stage vehicle.

Manufacturer: STA. Launches: 5. First Launch Date: 1965-11-17. Last Launch Date: 1969-09-20. Apogee: 20 km (12 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 100 kg (220 lb). Core Diameter: 0.16 m (0.52 ft). Total Length: 4.00 m (13.10 ft).

  • Stage1: 1 x NAL-16-1. Gross Mass: 100 kg (220 lb). Empty Mass: 40 kg (88 lb). Motor: 1 x NAL-16. Thrust (vac): 10.000 kN (2,248 lbf). Burn time: 14 sec. Length: 3.90 m (12.70 ft). Diameter: 0.17 m (0.54 ft). Propellants: Solid.
Version:

S-160. Status: Retired 1972.

Single stage vehicle.

Manufacturer: Nissan. Launches: 23. First Launch Date: 1964-07-28. Last Launch Date: 1972-04-16. Apogee: 80 km (49 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 100 kg (220 lb). Core Diameter: 0.16 m (0.52 ft). Total Length: 4.00 m (13.10 ft).

  • Stage1: 1 x S-160-1. Gross Mass: 100 kg (220 lb). Motor: 1 x S-160. Length: 3.90 m (12.70 ft). Diameter: 0.16 m (0.52 ft). Propellants: Solid.
Version:

S-210. Status: Retired 1982.

Single stage ionospheric sounding rocket used for research from Japan's Antarctic base.

The S-210 (S for single stage; 210 for 210 mm diameter) rocket was designed for low-cost observations of the ionosphere above 100 km altitude. The S-160 sub-scale version of the rocket proved the design concepts. The first two launches of the full sized versions in 1966-1967, .PT-210-1 and -2, were failures, with the motor case burning through. After redesign of the case and improved quality control, S-210-1 and -2 were successfully launched in August 1969. Following further successful tests in Japan in 1970-1971, the rocket was cleared for intensive use at the Japanese Antarctic base at Syowa in 1972-1978.

The rocket motor used butadiene propellant, which has good low temperature properties suited for use at the South Pole. The tapered circular grain provided 17 seconds of thrust. The combustion chamber was of chrome molybdenum steel, protected by a phenol resin-quartz glass fiber ablative covering. Stabilization was by a spin motor that produced 2 revolutions-per-second.

Manufacturer: Nissan. Launches: 47. Success Rate: 100.00%. First Launch Date: 1966-08-06. Last Launch Date: 1982-09-12. Apogee: 110 km (60 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 300 kg (660 lb). Core Diameter: 0.21 m (0.68 ft). Total Length: 5.20 m (17.00 ft).

  • Stage1: 1 x S-210-1. Gross Mass: 200 kg (440 lb). Motor: 1 x S-210. Length: 5.10 m (16.70 ft). Diameter: 0.21 m (0.68 ft). Propellants: Solid.
Version:

S-300 ISAS. Status: Retired 1969.

The the S-300, was developed for observations in Antarctica, in parallel with the S-210.

Although the vehicle reached 160 km altitude in its first flight in the fall of 1966, two out of three succeeding flights had stability problems. These were later attributed to an unusual increase of the attack angle due to pitch-roll resonance.

Manufacturer: ISAS. Launches: 4. Failures: 2. First Launch Date: 1966-11-04. Last Launch Date: 1969-09-08. Apogee: 160 km (90 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 600 kg (1,320 lb). Core Diameter: 0.30 m (0.98 ft). Total Length: 6.00 m (19.60 ft).

  • Stage1: 1 x S-300-1. Gross Mass: 500 kg (1,100 lb). Motor: 1 x S-300. Length: 6.00 m (19.60 ft). Diameter: 0.30 m (0.98 ft). Propellants: Solid.
Version:

BT-310. Status: Retired 1966.

Derivative of S-310.

Manufacturer: ISAS. Launches: 3. First Launch Date: 1966-04-28. Last Launch Date: 1966-08-06. Apogee: 5.00 km (3.10 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 700 kg (1,540 lb). Core Diameter: 0.31 m (1.01 ft). Total Length: 6.00 m (19.60 ft).

  • Stage1: 1 x BT-310-1. Gross Mass: 600 kg (1,320 lb). Motor: 1 x S-310. Length: 6.00 m (19.60 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.
Version:

S-310. Status: Active.

The S-310 was a mid-sized single-stage sounding rocket designed to reach an altitude of 200 km.

The S-310 went into a 2.8 deg/sec spin during ascent, induced by its canted tail fins. This eliminated the stability problem of the earlier S-300. The thrust programming was designed to peak half way through the burn, followed by a lower constant thrust burn through the maximum aerodynamic force portion of the ascent. This increased vehicle altitude, while relieving aerodynamic heating.

The chamber was made of chromium-molybdenum steel. The single CTPB composite propellant grain had two different wagon-wheel void configurations. The aft portion of the grain was consumed first, resulting in the dual-thrust profile. The tail fins were made of a solid titanium plate, with a composite ogive nose cone.

In the payload bay a yo-yo despin system, actuated 50 sec. after lift-off, reduced the spin to 1 deg/sec during the payload observation period.

The first flight of S-310 in January 1975 was successful, and it was later launched from both the Kagoshima Space Center at Uchinoura and Showa Station in Antarctica.

Manufacturer: ISAS. Launches: 45. Success Rate: 100.00%. First Launch Date: 1975-01-01. Last Launch Date: 2007-01-16. Apogee: 190 km (110 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 700 kg (1,540 lb). Core Diameter: 0.31 m (1.01 ft). Total Length: 6.80 m (22.30 ft).

  • Stage1: 1 x S-310-1. Gross Mass: 600 kg (1,320 lb). Motor: 1 x S-310. Length: 7.10 m (23.20 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.
Version:

S-520. Status: Retired 1998.

The S-520 was a larger single-stage rocket which could be equipped with a three-axis attitude control and a recovery system. It had the capability of launching a 100 kg payload above 300 km and provided more than five minutes of micro-gravity flight for experiments.

The S-520 was developed to replace the K-9M and K-10 type sounding rockets, and succeeded in doubling the payload capability of the K-9M by applying high-performance propellant, an optimum thrust program and a lightweight structure. The thrust program and stabilization strategy of the earlier S-310 was adopted, which had delivered stable flight performance since its first flight early in 1980.

The S-520 offered simplified flight operations since staging was eliminated, reduction of impact-related maritime safety, and reduction of launch cost.

The HTPB composite propellant grain was cast and molded in the case in the same way as the first stage of Mu launch vehicles. The single propellant grain provided a dual-thrust profile similar to the S-310's. The forward portion of the grain had a seven pointed gear configuration, resulting in an initial period of high thrust, while the aft portion of the grain had a simple tubular design for a sustained lower level thrust period. The nozzle's expansion ratio of 8:1 was designed to improve the effective specific impulse. The chamber was made of high tensile steel HT-140. For weight saving and heat resistance, the leading edges of the tail fins were made of titanium alloy and their body was an aluminum honeycomb sandwich plate with composite laminated surface plates.

Scientific instruments were stored inside a composite nose fairing, and common instruments just below. As an option, an attitude control module or recovery module could be installed between the common instruments and the rocket motor.

The fourth flight carried out payload retrieval, and the third flight, launched later than the fourth, performed attitude control of the nose by a hydrazine side jet system. The attitude outside the atmosphere normally was stabilized by a 2.2 deg/sec spin induced by the canted tail fins of the first stage. In this mission the last stage was despun using a yo-yo system.

Manufacturer: Nissan. Launches: 22. Failures: 1. First Launch Date: 1980-01-18. Last Launch Date: 1998-01-31. Apogee: 430 km (260 mi). Liftoff Thrust: 143.000 kN (32,147 lbf). Total Mass: 2,200 kg (4,800 lb). Core Diameter: 0.52 m (1.70 ft). Total Length: 9.00 m (29.50 ft).

  • Stage1: 1 x SS-520-1. Gross Mass: 2,300 kg (5,000 lb). Empty Mass: 400 kg (880 lb). Motor: 1 x S-520. Thrust (vac): 143.100 kN (32,170 lbf). Burn time: 29 sec. Length: 5.90 m (19.30 ft). Diameter: 0.52 m (1.70 ft). Propellants: Solid.
Version:

SS-520. Test vehicle. Status: Active.

The SS-520 was a two-stage rocket, the first stage consisting of the main booster of the S-520. It had a capability of launching a 140 kg payload to an altitude of about 1,000 km, and with addition of a third stage, as a satellite launch vehicle.

The SS-520 was a two-stage rocket, the first stage consisting of the main booster of the S-520. It had a capability of launching a 140 kg payload to an altitude of about 1,000 km.

Manufacturer: Nissan. Launches: 2. First Launch Date: 1998-02-05. Last Launch Date: 2000-12-04. Apogee: 1,000 km (600 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,600 kg (5,700 lb). Core Diameter: 0.52 m (1.70 ft). Total Length: 9.70 m (31.80 ft).

  • Stage1: 1 x SS-520-1. Gross Mass: 2,300 kg (5,000 lb). Empty Mass: 400 kg (880 lb). Motor: 1 x S-520. Thrust (vac): 143.100 kN (32,170 lbf). Burn time: 29 sec. Length: 5.90 m (19.30 ft). Diameter: 0.52 m (1.70 ft). Propellants: Solid.
  • Stage2: 1 x SS-520-2. Gross Mass: 400 kg (880 lb). Empty Mass: 111 kg (244 lb). Motor: 1 x SS-520. Length: 1.70 m (5.50 ft). Diameter: 0.52 m (1.70 ft). Propellants: Solid.
Version:

NAL-7. Test vehicle. Status: Retired 1970.

Single stage vehicle.

Manufacturer: STA. Launches: 2. First Launch Date: 1969-09-20. Last Launch Date: 1970-09-07. Apogee: 20 km (12 mi). Liftoff Thrust: 0 N ( lbf). Core Diameter: 0.0700 m (0.2290 ft).

Version:

NAL-25. Test vehicle. Status: Retired 1969.

Single stage vehicle.

Manufacturer: STA. Launches: 1. First Launch Date: 1969-02-01. Last Launch Date: 1969-02-01. Apogee: 20 km (12 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 100 kg (220 lb). Core Diameter: 0.25 m (0.82 ft).

Version:

NAL-735. Test vehicle. Status: Active.

Manufacturer: ISAS. Launches: 2. Failures: 1. First Launch Date: 2002-07-14. Last Launch Date: 2005-10-09. Apogee: 18 km (11 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 4,700 kg (10,300 lb). Core Diameter: 0.74 m (2.42 ft). Total Length: 10.00 m (32.00 ft).

  • Stage1: 1 x NAL-735-1. Gross Mass: 4,700 kg (10,300 lb). Motor: 1 x NAL-735. Thrust (vac): 250.000 kN (56,200 lbf). Burn time: 49 sec. Length: 9.00 m (29.50 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
Version:

TT-200.

Single stage vehicle.

Manufacturer: NASDA. Apogee: 100 km (60 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 200 kg (440 lb). Core Diameter: 0.20 m (0.65 ft). Total Length: 6.00 m (19.60 ft).

  • Stage1: 1 x TT-200-1. Gross Mass: 200 kg (440 lb). Motor: 1 x TT-200. Length: 5.00 m (16.40 ft). Diameter: 0.20 m (0.65 ft). Propellants: Solid.
Version:

TT-210. Status: Retired 1976.

Single stage vehicle.

Manufacturer: NASDA. Launches: 3. First Launch Date: 1975-08-17. Last Launch Date: 1976-09-24. Apogee: 100 km (60 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 200 kg (440 lb). Core Diameter: 0.21 m (0.68 ft). Total Length: 6.00 m (19.60 ft).

  • Stage1: 1 x TT-210-1. Gross Mass: 200 kg (440 lb). Motor: 1 x TT-210. Length: 5.30 m (17.30 ft). Diameter: 0.21 m (0.68 ft). Propellants: Solid.
Version:

TT-500.
TT-500
Credit - NASDA
Status: Retired 1980. Other Designations: TT-500A.

Small, half-meter diameter, two stage suborbital rocket used for tracking system and microgravity tests.

TT-500 launches 1 to 7 were tests of the design, used to validate the launch site system's tracking function. The TT-500A rocket was an improved version with experiment equipment in the payload section. It was used in launches 8 to 13, between 1980 and 1983, for space materials experiments. It was launched on ballistic, parabolic flights producing about seven minutes of microgravity, during which metal melting and solidifying, semiconductor and amorphous semiconductor, manufacturing compound and other experiments were conducted.

Manufacturer: NASDA. Launches: 7. First Launch Date: 1977-01-25. Last Launch Date: 1980-01-28. Apogee: 300 km (180 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,200 kg (4,800 lb). Core Diameter: 0.50 m (1.64 ft). Total Length: 10.50 m (34.40 ft).

  • Stage1: 1 x TT-500-1. Gross Mass: 1,300 kg (2,800 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x TT-500. Thrust (vac): 116.000 kN (26,077 lbf). Length: 7.00 m (22.90 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.
  • Stage2: 1 x TT-500-2. Gross Mass: 700 kg (1,540 lb). Empty Mass: 200 kg (440 lb). Motor: 1 x TT-500-S2. Thrust (vac): 61.000 kN (13,713 lbf). Length: 3.00 m (9.80 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.
Version:

TT-500A. Status: Retired 1983.

Manufacturer: NASDA. Launches: 6. First Launch Date: 1980-09-13. Last Launch Date: 1983-08-18. Apogee: 290 km (180 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,200 kg (4,800 lb). Core Diameter: 0.50 m (1.64 ft). Total Length: 10.50 m (34.40 ft).

  • Stage1: 1 x TT-500-1. Gross Mass: 1,300 kg (2,800 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x TT-500. Thrust (vac): 116.000 kN (26,077 lbf). Length: 7.00 m (22.90 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.
  • Stage2: 1 x TT-500-2. Gross Mass: 700 kg (1,540 lb). Empty Mass: 200 kg (440 lb). Motor: 1 x TT-500-S2. Thrust (vac): 61.000 kN (13,713 lbf). Length: 3.00 m (9.80 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.
S Chronology

1963 August 10 - 04:58 GMT - Niijima -. S-A1 Test mission Agency: STA. Apogee: 50 km (31 mi).

1963 August 10 - 07:20 GMT - Niijima -. S-A2 Test mission Agency: STA. Apogee: 50 km (31 mi).

1963 August 10 - 08:58 GMT - Niijima -. S-A3 Test mission Agency: STA. Apogee: 50 km (31 mi).

1964 July 17 - 07:20 GMT - Niijima -. S-B S-B1 Test mission Agency: STA. Apogee: 75 km (46 mi).

1964 July 19 - 03:47 GMT - Niijima -. S-B S-B2 Test mission Agency: STA. Apogee: 75 km (46 mi).

1964 July 23 - 03:37 GMT - Niijima -. S-B S-B3 Test mission Agency: STA. Apogee: 75 km (46 mi).

1964 July 28 - 02:08 GMT - Kagoshima -. S-160 PT-160-1 Propellant test Agency: ISAS. Apogee: 44 km (27 mi).

1965 June 15 - 02:30 GMT - Niijima -. S-B S-B4 Test mission Agency: STA. Apogee: 75 km (46 mi).

1965 June 16 - 04:00 GMT - Niijima -. S-B S-B5 Test mission Agency: STA. Apogee: 75 km (46 mi).

1965 June 17 - 07:30 GMT - Niijima -. HM-16 HM-16-D Test mission Agency: STA. Apogee: 52 km (32 mi).

1965 June 18 - 07:43 GMT - Niijima -. HM-16 HM-16-IT Test mission Agency: STA. Apogee: 38 km (23 mi).

1965 July 21 - 02:23 GMT - Kagoshima -. S-160 ST-160-1 Spin test Agency: ISAS. Apogee: 9.00 km (5.50 mi).

1965 July 21 - 05:20 GMT - Kagoshima -. S-160 ST-160-2 Test mission Agency: ISAS. Apogee: 14 km (8 mi).

1965 August 25 - 00:15 GMT - Kagoshima -. S-160 BT-160-1 Booster test Agency: ISAS. Apogee: 2.00 km (1.20 mi).

1965 August 25 - 02:09 GMT - Kagoshima -. S-160 BT-160-2 Booster test Agency: ISAS. Apogee: 9.00 km (5.50 mi).

1965 November 1 - 02:15 GMT - Kagoshima -. S-160 PT-160-2 Propellant test Agency: ISAS. Apogee: 93 km (57 mi).

1965 November 4 - 07:25 GMT - Kagoshima -. S-160 DS-160-1 Despin test Agency: ISAS. Apogee: 35 km (21 mi).

1965 November 16 - 02:09 GMT - Niijima -. ST ST-I F1 Test mission Agency: STA. Apogee: 20 km (12 mi).

1965 November 17 - 06:34 GMT - Niijima -. NAL-16 NAL-16TR Test mission Agency: STA. Apogee: 45 km (27 mi).

1965 November 18 - 06:42 GMT - Niijima -. S-B SB-II F6 Test mission Agency: STA. Apogee: 75 km (46 mi).

1965 November 19 - 01:44 GMT - Niijima -. S-B SB-II F7 Test mission Agency: STA. Apogee: 75 km (46 mi).

1966 April 25 - 04:15 GMT - Kagoshima -. S-160 IT-160-1 Instrument test Agency: ISAS. Apogee: 68 km (42 mi).

1966 April 28 - 02:00 GMT - Kagoshima -. BT-310 BT-310-1 Test mission Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1966 April 29 - 00:00 GMT - Kagoshima -. BT-310 BT-310-2 Test mission Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1966 August 6 - 02:00 GMT - Kagoshima -. BT-310 MM-310-1 Mu Scale Model test Agency: ISAS. Apogee: 2.00 km (1.20 mi).

1966 August 6 - 06:30 GMT - Kagoshima -. S-210 PT-210-1 Test mission Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1966 November 4 - 02:05 GMT - Kagoshima -. LV Model: S-300 ISAS . S-300 PT-300-1 Test mission Agency: ISAS. Apogee: 160 km (90 mi).

1967 - Tanegashima T. NAL-16 NAL-16TR Test mission Agency: STA. Apogee: 45 km (27 mi).

1967 January 24 - 08:00 GMT - Kagoshima -. S-160 MT-160-001 Meteorological Test Aeronomy mission Agency: ISAS. Apogee: 86 km (53 mi).

1967 January 27 - 02:15 GMT - Kagoshima -. S-160 IT-160-2 Instrument test Agency: ISAS. Apogee: 86 km (53 mi).

1967 March 11 - 06:30 GMT - Kagoshima -. S-210 PT-210-2 Test mission Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1968 September 10 - Kagoshima -. S-160 ST-160-F-1 Test mission Agency: ISAS. Apogee: 80 km (49 mi).

1968 September 10 - Kagoshima -. S-160 ST-160-F-2 Test mission Agency: ISAS. Apogee: 80 km (49 mi).

1968 September 12 - Kagoshima -. S-160 SO-160-1 Test mission Agency: ISAS. Apogee: 80 km (49 mi).

1968 September 14 - 01:00 GMT - Kagoshima -. S-160-1 Aeronomy mission Agency: ISAS. Apogee: 82 km (50 mi).

1968 September 14 - 04:00 GMT - Kagoshima -. S-160-2 Aeronomy mission Agency: ISAS. Apogee: 82 km (50 mi).

1968 September 17 - 07:10 GMT - Tanegashima T. SA-II SA-II A9 Test mission Agency: STA. Apogee: 20 km (12 mi).

1968 September 19 - 07:01 GMT - Tanegashima T. NAL-16 NAL-16H F1 Test mission Agency: STA. Apogee: 100 km (60 mi).

1969 January 9 - Kagoshima -. LV Model: S-300 ISAS . S-300-1 FAILURE: Failure. Aeronomy mission Agency: ISAS. Apogee: 0 km ( mi).

1969 January 30 - 01:31 GMT - Tanegashima T. NAL-16 NAL-16 31D Test mission Agency: STA. Apogee: 50 km (31 mi).

1969 February 1 - 01:40 GMT - Tanegashima T. NAL-25 NAL-25 31 Test mission Agency: STA. Apogee: 50 km (31 mi).

1969 February 7 - 06:30 GMT - Tanegashima T. S-C SC-3 Test mission Agency: STA. Apogee: 85 km (52 mi).

1969 February 8 - 01:30 GMT - Tanegashima T. S-C SC-4 Test mission Agency: STA. Apogee: 85 km (52 mi).

1969 February 8 - 06:30 GMT - Tanegashima T. S-C SC-1 Test mission Agency: STA. Apogee: 85 km (52 mi).

1969 August 7 - Kagoshima -. S-210-1 Plasma / fields / x-ray astronomy mission Agency: ISAS. Apogee: 101 km (62 mi).

1969 August 8 - 12:00 GMT - Kagoshima -. S-210-2 X-ray astronomy mission Agency: ISAS. Apogee: 108 km (67 mi).

1969 August 24 - Kagoshima -. LV Model: S-300 ISAS . S-300-2 Test mission Agency: ISAS. Apogee: 160 km (90 mi).

1969 August 25 - Kagoshima -. S-160 IT-160-3 Instrumentation Test Aeronomy mission Agency: ISAS. Apogee: 78 km (48 mi).

1969 September 8 - 10:20 GMT - Kagoshima -. LV Model: S-300 ISAS . S-300-3 FAILURE: Failure. Aeronomy mission Agency: ISAS. Apogee: 10 km (6 mi).

1969 September 9 - 06:30 GMT - Tanegashima T. S-B SB-III F11 Test mission Agency: STA. Apogee: 75 km (46 mi).

1969 September 15 - 01:40 GMT - Tanegashima T. JCR-1 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1969 September 16 - 06:40 GMT - Tanegashima T. JCR-2 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1969 September 20 - 01:55 GMT - Tanegashima T. NAL-16 NAL-16H F2 Test mission Agency: STA. Apogee: 100 km (60 mi).

1969 September 20 - 06:30 GMT - Tanegashima T. NAL-7 NAL-7 F7 Test mission Agency: STA. Apogee: 20 km (12 mi).

1970 January 17 - 01:20 GMT - Kagoshima -. S-210-3 X-ray astronomy mission Agency: ISAS. Apogee: 119 km (73 mi).

1970 January 23 - 05:00 GMT - Kagoshima -. S-160 MT-160-2 Meteorological Test Aeronomy mission Agency: ISAS. Apogee: 75 km (46 mi).

1970 February 1 - 01:00 GMT - Tanegashima T. JCR-3 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1970 February 4 - Tanegashima T. JCR-4 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1970 February 10 - 12:30 GMT - Syowa Base -. S-160JA-1 Auroral mission Agency: NIPR. Apogee: 87 km (54 mi).

1970 February 17 - 12:10 GMT - Syowa Base -. S-160JA-2 Auroral mission Agency: NIPR. Apogee: 88 km (54 mi).

1970 September 7 - 06:30 GMT - Tanegashima T. NAL-7 NAL-7 BS9 Test mission Agency: STA. Apogee: 20 km (12 mi).

1970 September 28 - 01:20 GMT - Kagoshima -. S-210-5 Ionosphere mission Agency: ISAS. Apogee: 108 km (67 mi).

1971 January 16 - 02:00 GMT - Kagoshima -. S-210-4 Ionosphere mission Agency: ISAS. Apogee: 115 km (71 mi).

1971 February 1 - 01:30 GMT - Tanegashima T. JCR-5 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1971 February 3 - 01:35 GMT - Tanegashima T. S-B SB-III A12 Test mission Agency: STA. Apogee: 75 km (46 mi).

1971 February 3 - 06:30 GMT - Tanegashima T. S-B SB-III A13 Test mission Agency: STA. Apogee: 75 km (46 mi).

1971 April 30 - 10:00 GMT - Syowa Base -. S-160JA-3 Auroral mission Agency: NIPR. Apogee: 83 km (51 mi).

1971 June 24 - 01:05 GMT - Syowa Base -. S-210JA-4 Auroral mission Agency: NIPR. Apogee: 130 km (80 mi).

1971 July 21 - 21:52 GMT - Syowa Base -. S-210JA-3 Auroral mission Agency: NIPR. Apogee: 131 km (81 mi).

1971 August 10 - 02:24 GMT - Syowa Base -. S-210JA-1 Auroral mission Agency: NIPR. Apogee: 139 km (86 mi).

1971 September 6 - 01:35 GMT - Tanegashima T. S-B SB-III A14 Test mission Agency: STA. Apogee: 75 km (46 mi).

1971 September 11 - 01:45 GMT - Tanegashima T. S-B SB-III A15 Test mission Agency: STA. Apogee: 75 km (46 mi).

1971 September 13 - 21:50 GMT - Syowa Base -. S-210JA-5 Auroral mission Agency: NIPR. Apogee: 115 km (71 mi).

1971 September 17 - 06:40 GMT - Tanegashima T. JCR-6 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1971 September 24 - 21:08 GMT - Syowa Base -. S-210JA-2 Auroral mission Agency: NIPR. Apogee: 138 km (85 mi).

1971 September 29 - Kagoshima -. S-160-3 Parachute test Agency: ISAS. Apogee: 80 km (49 mi).

1971 December 3 - 12:00 GMT - Syowa Base -. S-210JA-6 Auroral mission Agency: NIPR. Apogee: 131 km (81 mi).

1972 January 21 - 02:24 GMT - Kagoshima -. S-210-6 Ionosphere mission Agency: ISAS. Apogee: 112 km (69 mi).

1972 January 29 - Kagoshima -. S-210 DT-210-1 Structural Dynamics test Agency: ISAS. Apogee: 100 km (60 mi).

1972 February 6 - 06:35 GMT - Tanegashima T. JCR-7 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1972 February 11 - 12:00 GMT - Syowa Base -. S-210JA-12 Mass spectrometer Ionosphere mission Agency: NIPR. Apogee: 108 km (67 mi).

1972 February 17 - 08:00 GMT - Kagoshima -. S-210-7 Ionosphere mission Agency: ISAS. Apogee: 118 km (73 mi).

1972 February 21 - 02:00 GMT - Kagoshima -. S-160-4 Fields mission Agency: ISAS. Apogee: 81 km (50 mi).

1972 April 16 - 23:42 GMT - Syowa Base -. S-160JA-4 Ionosphere mission Agency: NIPR. Apogee: 86 km (53 mi).

1972 May 13 - 23:13 GMT - Syowa Base -. S-210JA-9 Aurora / ionosphere / fields mission Agency: NIPR. Apogee: 129 km (80 mi).

1972 May 15 - 23:02 GMT - Syowa Base -. S-210JA-10 Aurora / ionosphere / fields mission Agency: NIPR. Apogee: 115 km (71 mi).

1972 August 7 - 01:45 GMT - Syowa Base -. S-210JA-11 Aurora / ionosphere / fields mission Agency: NIPR. Apogee: 126 km (78 mi).

1972 August 11 - 01:01 GMT - Syowa Base -. S-210JA-8 Ionosphere / fields mission Agency: NIPR. Apogee: 127 km (78 mi).

1972 December 13 - 21:23 GMT - Syowa Base -. S-210JA-7 Aurora / ionosphere / fields mission Agency: NIPR. Apogee: 126 km (78 mi).

1973 January 15 - 23:40 GMT - Kagoshima -. S-210-8 Ionosphere mission Agency: ISAS. Apogee: 122 km (75 mi).

1973 February 7 - 01:50 GMT - Tanegashima T. JCR-8 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1973 February 14 - 20:45 GMT - Syowa Base -. S-210JA-16 Auroral mission Agency: NIPR. Apogee: 103 km (64 mi).

1973 March 25 - 17:47 GMT - Syowa Base -. S-210JA-14 Auroral mission Agency: NIPR. Apogee: 114 km (70 mi).

1973 April 22 - 18:25 GMT - Syowa Base -. S-210JA-17 Auroral mission Agency: NIPR. Apogee: 124 km (77 mi).

1973 June 10 - 17:20 GMT - Syowa Base -. S-210JA-13 Auroral mission Agency: NIPR. Apogee: 123 km (76 mi).

1973 June 11 - 18:10 GMT - Syowa Base -. S-210JA-15 Auroral mission Agency: NIPR. Apogee: 125 km (77 mi).

1973 July 15 - 16:09 GMT - Syowa Base -. S-210JA-19 Auroral mission Agency: NIPR. Apogee: 131 km (81 mi).

1973 August 19 - 09:55 GMT - Kagoshima -. S-210-9 Aeronomy mission Agency: ISAS. Apogee: 115 km (71 mi).

1973 August 22 - 21:53 GMT - Syowa Base -. S-210JA-18 Auroral arc Aurora mission Agency: NIPR. Apogee: 129 km (80 mi).

1973 September 7 - 01:40 GMT - Tanegashima T. JCR-9 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1974 February 1 - 06:30 GMT - Tanegashima T. JCR-10 Test mission Agency: NASDA. Apogee: 200 km (120 mi).

1974 August 20 - 09:55 GMT - Kagoshima -. S-210-10 NNP / NEL / TEL Aeronomy / ionosphere mission Agency: ISAS. Apogee: 112 km (69 mi).

1975 January 1 - Kagoshima -. S-310-1 Test mission Agency: ISAS. Apogee: 200 km (120 mi).

1975 August 17 - 06:00 GMT - Tanegashima T. TT-210 TT-210-1F Test mission Agency: NASDA. Apogee: 100 km (60 mi).

1975 August 30 - 04:10 GMT - Kagoshima -. S-310-2 Ionosphere mission Agency: ISAS. Apogee: 191 km (118 mi).

1976 January 25 - 23:20 GMT - Syowa Base -. S-210JA-22 NO / Ne Aeronomy / ionosphere mission Agency: NIPR. Apogee: 127 km (78 mi).

1976 January 27 - 06:00 GMT - Tanegashima T. TT-210 TT-210-2F Test mission Agency: NASDA. Apogee: 100 km (60 mi).

1976 February 13 - 09:45 GMT - Syowa Base -. S-310JA-1 VLF / HF Ionosphere mission Agency: NIPR. Apogee: 216 km (134 mi).

1976 June 24 - 23:40 GMT - Syowa Base -. S-210JA-20 VLF / HF / ne Aurora mission Agency: NIPR. Apogee: 118 km (73 mi).

1976 July 26 - 00:23 GMT - Syowa Base -. S-210JA-21 VLF / HF / ne / ISIS-2 Aurora mission Agency: NIPR. Apogee: 116 km (72 mi).

1976 August 16 - 23:54 GMT - Syowa Base -. S-210JA-24 E / B / ne Aurora mission Agency: NIPR. Apogee: 118 km (73 mi).

1976 August 17 - 10:15 GMT - Kagoshima -. S-210-11 Aeronomy / ionosphere mission Agency: ISAS. Apogee: 112 km (69 mi).

1976 August 21 - 12:10 GMT - Kagoshima -. S-310-3 Ionosphere mission Agency: ISAS. Apogee: 195 km (121 mi).

1976 September 1 - 00:00 GMT - Syowa Base -. S-210JA-25 E / B / ne Aurora mission Agency: NIPR. Apogee: 125 km (77 mi).

1976 September 13 - 04:31 GMT - Syowa Base -. S-210JA-23 NO / Ne / ISIS-2 Aurora mission Agency: NIPR. Apogee: 120 km (70 mi).

1976 September 24 - 01:30 GMT - Tanegashima T. TT-210 TT-210-3F Test mission Agency: NASDA. Apogee: 100 km (60 mi).

1977 January 25 - 01:30 GMT - Tanegashima T. TT-500 TT-500-1F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1977 February 10 - 00:22 GMT - Syowa Base -. S-310JA-2 VLF / HF Ionosphere mission Agency: NIPR. Apogee: 212 km (131 mi).

1977 March 27 - 03:55 GMT - Syowa Base -. S-210JA-28 NO / O3 / Ne Aeronomy mission Agency: NIPR. Apogee: 106 km (65 mi).

1977 April 11 - 05:00 GMT - Syowa Base -. S-210JA-26 NO / O3 / Ne Aeronomy mission Agency: NIPR. Apogee: 105 km (65 mi).

1977 July 12 - 16:15 GMT - Syowa Base -. S-210JA-29 E / B / ne / ISIS-2 Aurora mission Agency: NIPR. Apogee: 118 km (73 mi).

1977 July 26 - 15:35 GMT - Syowa Base -. S-310JA-3 VLF / plasma / B Ionosphere mission Agency: NIPR. Apogee: 221 km (137 mi).

1977 August 10 - 12:47 GMT - Syowa Base -. S-210JA-27 NO airglow Aurora mission Agency: NIPR. Apogee: 120 km (70 mi).

1977 August 25 - 01:30 GMT - Tanegashima T. TT-500 TT-500-2F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1977 September 15 - 09:30 GMT - Kagoshima -. S-210-12 Aeronomy / ionosphere mission Agency: ISAS. Apogee: 114 km (70 mi).

1977 September 21 - 08:35 GMT - Kagoshima -. S-310-4 Ionosphere mission Agency: ISAS. Apogee: 188 km (116 mi).

1978 January 16 - 01:30 GMT - Tanegashima T. TT-500 TT-500-3F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1978 January 28 - 20:20 GMT - Syowa Base -. S-210JA-30 Aurora mission Agency: NIPR. Apogee: 125 km (77 mi).

1978 February 6 - 18:55 GMT - Syowa Base -. S-210JA-31 Aurora mission Agency: NIPR. Apogee: 116 km (72 mi).

1978 August 25 - 01:30 GMT - Tanegashima T. TT-500 TT-500-4F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1979 January 19 - 08:50 GMT - Kagoshima -. S-310-6 Aeronomy / ionosphere mission Agency: ISAS. Apogee: 212 km (131 mi).

1979 January 27 - 01:30 GMT - Tanegashima T. TT-500 TT-500-5F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1979 January 31 - 02:00 GMT - Kagoshima -. S-310-5 Ionosphere / fields mission Agency: ISAS. Apogee: 185 km (114 mi).

1979 August 25 - 01:40 GMT - Tanegashima T. TT-500 TT-500-6F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1979 September 15 - 11:00 GMT - Kagoshima -. S-310-7 Aeronomy mission Agency: ISAS. Apogee: 166 km (103 mi).

1980 January 18 - 06:20 GMT - Kagoshima L. S-520-1 Heat Pipe Aeronomy / ionosphere mission Agency: ISAS. Apogee: 329 km (204 mi).

1980 January 28 - 01:30 GMT - Tanegashima T. TT-500 TT-500-7F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1980 February 2 - 08:47 GMT - Kagoshima -. S-310-8 Aeronomy mission Agency: ISAS. Apogee: 179 km (111 mi).

1980 September 13 - 22:00 GMT - Tanegashima T. TT-500A TT-500A-8F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1981 January 14 - 22:00 GMT - Tanegashima T. TT-500A TT-500A-9F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1981 January 21 - 21:46 GMT - Kagoshima -. S-310-9 Aeronomy mission Agency: ISAS. Apogee: 174 km (108 mi).

1981 January 29 - 07:00 GMT - Kagoshima L. S-520-2 TPE-2 Ionosphere / tether mission Agency: ISAS. Apogee: 323 km (200 mi).

1981 August 1 - 22:00 GMT - Tanegashima T. TT-500A TT-500A-10F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1981 August 24 - 12:00 GMT - Kagoshima -. S-310-10 Test / aurora / aeronomy mission Agency: ISAS. Apogee: 187 km (116 mi).

1981 September 5 - 01:00 GMT - Kagoshima L. S-520-4 Payload recovery rest / ionosphere mission Agency: ISAS. Apogee: 224 km (139 mi).

1981 September 7 - 09:38 GMT - Kagoshima -. S-310-11 Submillimeter atmospheric spectra Aeronomy mission Agency: ISAS. Apogee: 193 km (119 mi).

1982 February 14 - 10:50 GMT - Kagoshima L. S-520-3 0.3m telescope test Ultraviolet astronomy mission Agency: ISAS. Apogee: 266 km (165 mi).

1982 August 15 - 23:15 GMT - Tanegashima T. TT-500A TT-500A-11F Test mission Agency: NASDA. Apogee: 300 km (180 mi).

1982 September 6 - 02:00 GMT - Kagoshima L. S-520-5 0.1m telescope Solar extreme ultraviolet mission Agency: ISAS. Apogee: 237 km (147 mi).

1982 September 12 - 12:00 GMT - Kagoshima -. S-210-13 Aeronomy mission Agency: ISAS. Apogee: 97 km (60 mi).

1982 September 25 - 09:15 GMT - Kagoshima -. S-310-12 Aeronomy mission Agency: ISAS. Apogee: 200 km (120 mi).

1983 January 26 - 23:00 GMT - Tanegashima T. TT-500A TT-500A-12F Microgravity mission Agency: NASDA. Apogee: 300 km (180 mi).

1983 August 18 - 23:00 GMT - Tanegashima T. TT-500A TT-500A-13F Microgravity mission Agency: NASDA. Apogee: 300 km (180 mi).

1983 August 29 - 10:00 GMT - Kagoshima L. S-520-6 MINIX Plasma physics mission Agency: ISAS. Apogee: 238 km (147 mi).

1983 September 12 - 22:00 GMT - Kagoshima -. S-310-13 Ionosphere mission Agency: ISAS. Apogee: 227 km (141 mi).

1983 September 16 - 18:16 GMT - Kagoshima -. S-310-14 Aeronomy mission Agency: ISAS. Apogee: 218 km (135 mi).

1984 April 4 - 19:27 GMT - Syowa Base -. S-310JA-8 Ionosphere mission Agency: NIPR. Apogee: 201 km (124 mi).

1984 May 3 - 22:14 GMT - Syowa Base -. S-310JA-9 Ionosphere mission Agency: NIPR. Apogee: 204 km (126 mi).

1984 May 28 - 23:17 GMT - Syowa Base -. S-310JA-10 Ionosphere mission Agency: NIPR. Apogee: 209 km (129 mi).

1985 February 7 - 09:00 GMT - Kagoshima L. S-310-15 Aeronomy mission Agency: ISAS. Apogee: 213 km (132 mi).

1985 February 11 - 10:30 GMT - Kagoshima L. S-520-7 Aeronomy / ionosphere mission Agency: ISAS. Apogee: 362 km (224 mi).

1985 May 29 - 00:59 GMT - Syowa Base -. S-310JA-11 Ionosphere mission Agency: NIPR. Apogee: 212 km (131 mi).

1985 July 12 - 19:35 GMT - Syowa Base -. S-310JA-12 Ionosphere mission Agency: NIPR. Apogee: 222 km (137 mi).

1986 February 1 - 12:40 GMT - Kagoshima L. S-310-16 E-region Ionosphere mission Agency: ISAS. Apogee: 201 km (124 mi).

1986 September 6 - 13:00 GMT - Kagoshima L. S-310-17 Airglow Aeronomy mission Agency: ISAS. Apogee: 202 km (125 mi).

1987 January 15 - 08:10 GMT - Kagoshima L. S-520-9 E field Ionosphere / aeronomy mission Agency: ISAS. Apogee: 365 km (226 mi).

1987 February 21 - 16:15 GMT - Kagoshima L. S-520-8 GUV Ultraviolet astronomy mission Agency: ISAS. Apogee: 286 km (177 mi).

1988 January 28 - 02:00 GMT - Kagoshima L. S-310-18 D-region Ionosphere / aeronomy mission Agency: ISAS. Apogee: 202 km (125 mi).

1989 February 1 - 12:00 GMT - Kagoshima L. S-310-19 Aeronomy mission Agency: ISAS. Apogee: 230 km (140 mi).

1989 September 4 - 16:15 GMT - Kagoshima L. S-520-10 CIR Cosmic infrared Infrared astronomy mission Agency: ISAS. Apogee: 288 km (178 mi).

1990 January 27 - 19:30 GMT - Kagoshima L. S-310-20 Aeronomy mission Agency: ISAS. Apogee: 185 km (114 mi).

1990 February 21 - 16:00 GMT - Kagoshima L. S-520-11 CIR Infrared astronomy mission Agency: ISAS. Apogee: 317 km (196 mi).

1990 February 26 - 02:06 GMT - Andoya -. S-520-12 Auroral mission Agency: ISAS. Apogee: 369 km (229 mi).

1991 February 12 - 03:29 GMT - Andoya -. S-520-14 Auroral mission Agency: ISAS. Apogee: 353 km (219 mi).

1991 February 16 - 13:00 GMT - Kagoshima L. S-520-13 Extreme ultraviolet Telescopes Extreme ultraviolet astronomy mission Agency: ISAS. Apogee: 337 km (209 mi).

1992 January 28 - 12:00 GMT - Kagoshima L. S-310-21 Aeronomy mission Agency: ISAS. Apogee: 223 km (138 mi).

1992 February 1 - 16:00 GMT - Kagoshima L. S-520-15 CIR Infrared astronomy mission Agency: ISAS. Apogee: 338 km (210 mi).

1993 February 18 - 07:00 GMT - Kagoshima L. S-520-16 METS Ionosphere / active plasma mission Agency: ISAS. Apogee: 272 km (169 mi).

1994 February 15 - 23:52 GMT - Andoya -. S-310-22 NNP / AIR / NID / NEL Aeronomy mission Agency: ISAS. Apogee: 192 km (119 mi).

1994 November 24 - 10:20 GMT - Andoya -. S-310-23 NNP / AIR / NID / NEL Aeronomy mission Agency: ISAS. Apogee: 200 km (120 mi).

1994 December 1 - 21:39 GMT - Andoya -. S-520-21 Auroral mission Agency: ISAS. Apogee: 344 km (213 mi).

1995 January 23 - 12:30 GMT - Kagoshima L. S-520-17 Submillimeter radio astronomy mission Agency: ISAS. Apogee: 346 km (214 mi).

1995 January 28 - 16:00 GMT - Kagoshima L. S-520-19 Extreme ultraviolet Telescopes Extreme ultraviolet astronomy mission Agency: ISAS. Apogee: 330 km (200 mi).

1995 September 17 - 07:30 GMT - Kagoshima L. S-520-20 FAILURE: Failure. Lunar Penetrator test technology mission Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1996 February 11 - 11:00 GMT - Kagoshima L. S-310-24 NTV-1 Aeronomy mission Agency: ISAS. Apogee: 199 km (123 mi).

1996 August 20 - 15:30 GMT - Kagoshima L. S-310-26 SEEK-1 Plasma mission Agency: ISAS. Apogee: 177 km (109 mi).

1996 August 26 - 14:00 GMT - Kagoshima L. S-310-25 SEEK-1 Plasma mission Agency: ISAS. Apogee: 180 km (110 mi).

1997 January 30 - 07:30 GMT - Kagoshima L. S-520-18 Lunar Penetrator test technology mission Agency: ISAS. Apogee: 309 km (192 mi).

1998 January 25 - 08:35 GMT - Kagoshima L. S-310-27 SEEK Ozone Aeronomy mission Agency: ISAS. Apogee: 183 km (113 mi).

1998 January 31 - 04:30 GMT - Kagoshima L. S-520-22 SOLAR-B XDT Solar x-ray / ultraviolet mission Agency: ISAS. Apogee: 270 km (160 mi).

1998 February 5 - 08:30 GMT - Kagoshima L. SS-520 SS-520-1 ENA / EPS / LAP Test / plasma mission Agency: ISAS. Apogee: 750 km (460 mi).

1999 February 2 - 01:30 GMT - Kagoshima L. S-310-28 SELENE RF / X-ray test Ionosphere / x-ray mission Agency: ISAS. Apogee: 184 km (114 mi).

2000 January 9 - 20:50 GMT - Kagoshima L. S-310-29 WAVE2000 Aeronomy mission Agency: ISAS. Apogee: 179 km (111 mi).

2000 December 4 - 09:16 GMT - SvalRak -. SS-520 SS-520-2 Ionosphere mission Agency: ISAS. Apogee: 1,108 km (688 mi).

2002 February 6 - 10:30 GMT - Kagoshima L. S-310-30 NTV-2 Thermosphere Aeronomy mission Agency: ISAS. Apogee: 150 km (90 mi).

2002 July 14 - 01:34 GMT - Woomera LA1. FAILURE: Failure. National Experimental Supersonic Transport NEXST-1 test Agency: NAL. Apogee: 0 km ( mi). The intention was that an 11.5-m-long, one tenth scale model of the aircraft would be propelled by the NAL-735 solid rocket booster to Mach 2 at 18 km altitude. Instead the vehicle lost stability and crashed near the launch point.

2002 August 3 - 14:24 GMT - Kagoshima L. S-310-31 SEEK-2 Aeronomy mission Agency: ISAS. Apogee: 152 km (94 mi).

2002 August 3 - 14:39 GMT - Kagoshima L. S-310-32 SEEK-2 Aeronomy mission Agency: ISAS. Apogee: 117 km (72 mi).

2004 January 17 - 15:30 GMT - Kagoshima L. S-310-33 WAVE2004 Aeronomy mission Agency: ISAS. Apogee: 141 km (87 mi).

2004 August 9 - 08:15 GMT - Kagoshima L. S-310-34 Solar Sails Technology mission Agency: ISAS. Apogee: 170 km (100 mi).

2004 December 13 - 00:33 GMT - Andoya U3. S-310-35 DELTA 2004 Aeronomy mission Agency: JAXA. Apogee: 140 km (80 mi).

2005 October 9 - 21:36 GMT - Woomera LA1. NEXST-1 F2 Agency: NAL. Apogee: 20 km (12 mi).

2006 January 22 - 04:00 GMT - Kagoshima L. S-310-36 Furoshiki Technology test Agency: JAXA. Apogee: 130 km (80 mi).

2007 January 16 - 02:20 GMT - Kagoshima L. S-310-37 Ionosphere mission Agency: JAXA. Apogee: 130 km (80 mi).

Bibliography:
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© Mark Wade, 1997 - 2008 except where otherwise noted.
S-310
Credit- JAXA