S-520 (original) (raw)
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S-520
Japanese sounding rocket. 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.
Status: Active. First Launch: 1980-01-18. Last Launch: 2015-09-11. Number: 31 . Thrust: 143.00 kN (32,147 lbf). Gross mass: 2,300 kg (5,000 lb). Unfuelled mass: 400 kg (880 lb). Burn time: 29 s. Height: 9.00 m (29.50 ft). Diameter: 0.52 m (1.70 ft). Apogee: 430 km (260 mi).
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.
More at: S-520.
Subtopics
| SS-520 Japanese test 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, and with addition of a third stage, as a satellite launch vehicle. |
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Country: Japan. Propellants: Solid. Launch Sites: Kagoshima, Andoya, Kagoshima L, Kagoshima K. Agency: ISAS, Nissan.
1980 January 18 - . 06:20 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1981 January 29 - . 07:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1981 September 5 - . 01:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
- Payload recovery rest / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 224 km (139 mi).
1982 February 14 - . 10:50 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
- 0.3m telescope test Ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 266 km (165 mi).
1982 September 6 - . 02:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
- 0.1m telescope Solar extreme ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 237 km (147 mi).
1983 August 29 - . 10:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1985 February 11 - . 10:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1987 January 15 - . 08:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1987 February 21 - . 16:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1989 September 4 - . 16:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
- CIR Cosmic infrared Infrared astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 288 km (178 mi).
1990 February 21 - . 16:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1990 February 26 - . 02:06 GMT - . Launch Site: Andoya. Launch Vehicle: S-520.
1991 February 12 - . 03:29 GMT - . Launch Site: Andoya. Launch Vehicle: S-520.
1991 February 16 - . 13:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
- Extreme ultraviolet Telescopes Extreme ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 337 km (209 mi).
1992 February 1 - . 16:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1993 February 18 - . 07:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1994 December 1 - . 21:39 GMT - . Launch Site: Andoya. Launch Vehicle: S-520.
1995 January 23 - . 12:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1995 January 28 - . 16:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
- Extreme ultraviolet Telescopes Extreme ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 330 km (200 mi).
1995 September 17 - . 07:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520. FAILURE: Failure.
- Lunar Penetrator test technology mission - . Nation: Japan. Agency: ISAS. Apogee: 1.00 km (0.60 mi).
1997 January 30 - . 07:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
1998 January 31 - . 04:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. Launch Vehicle: S-520.
- SOLAR-B XDT Solar x-ray / ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 270 km (160 mi).
1998 February 5 - . 08:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S-520. Launch Vehicle: SS-520.
2000 December 4 - . 09:16 GMT - . Launch Site: SvalRak. LV Family: S-520. Launch Vehicle: SS-520.
2007 September 2 - . 10:20 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima K. Launch Pad: Kagoshima LCK. Launch Vehicle: S-520.
2008 August 2 - . 08:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima K. Launch Pad: Kagoshima LCK. Launch Vehicle: S-520.
2010 August 30 - . 20:00 GMT - . Launch Site: Kagoshima. Launch Vehicle: S-520.
- S-520-25 - . Nation: Japan. Agency: JAXA. Apogee: 309 km (192 mi).
T-REX Tether Technology Rocket Experiment. The 580 kg payload consisted of three parts: 'mother' and 'daughter' spacecraft connected by a 300-meter-long electrodynamic tether; and the small Tethered Space Robot connected to the daughter. Fell into Pacific Ocean after a ten-minute zero-G flight.
2012 January 12 - . 14:51 GMT - . Launch Site: Kagoshima. Launch Vehicle: S-520.
- S-520-26 - . Nation: Japan. Apogee: 298 km (185 mi). Atmospheric science payload..
2012 December 17 - . 07:00 GMT - . Launch Site: Kagoshima. Launch Vehicle: S-520.
- S-520-28 - . Nation: Japan. Apogee: 312 km (193 mi). Microgravity experiments..
2013 July 20 - . 02:57 GMT - . Launch Site: Kagoshima. Launch Vehicle: S-520.
- S-520-27 - . Nation: Japan. Apogee: 316 km (196 mi). Atmospheric science mission..
2014 August 17 - . 10:10 GMT - . Launch Site: Kagoshima. Launch Vehicle: S-520.
- S-520-29 - . Nation: Japan. Apogee: 243 km (150 mi). Payload studied the sporadic E layer in the ionosphere..
2014 August 20 - . 10:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima K. Launch Vehicle: S-520.
2015 September 11 - . 11:00 GMT - . Launch Site: Kagoshima. Launch Vehicle: S-520.
- S-520-30 - . Nation: Japan. Apogee: 312 km (193 mi). Physics mission. Impacted Phillipine Sea..
2017 January 14 - . 23:33 GMT - . Launch Site: Tanegashima. Launch Complex: Kagoshima K. LV Family: S-520. Launch Vehicle: SS-520.
- TRICOM-1 - . Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. COSPAR: 2017-0F01. Apogee: 200 km (120 mi). Perigee: -6,340 km (-6,340 mi). Inclination: 30.00 deg.
See TRICOM 1. Japan attempted to launch a single cubesat into orbit with a launch vehicle massing less than 3 tonnes. The SS-520 sounding rocket was furnished with a 78 kg third stage which was intended to orbit a 3U, 3 kg cubesat, TRICOM-1. The mission was flight SS-520-4 (SS-520-1 and 2 were normal sounding rocket flights; 3 has not yet flown.) However, telemetry was lost 20 seconds into flight, during first stage burn. Following range safety rules, the command to ignite stage 2 was not sent and the vehicle flew a suborbital path to about 200 km altitude and then splashed down in the ocean. The record smallest successful orbital launch vehicle remains the 9.4-tonne Lambda 4S, also Japanese, which was retired in 1979.
2018 February 3 - . 05:03 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima K. LV Family: S-520. Launch Vehicle: SS-520.
- Tasuki - . Payload: TRICOM-1R; TRICOM-1R (TASUKI). Nation: Japan. USAF Sat Cat: 43201 . COSPAR: 2018-016A. Apogee: 256 km (159 mi). Perigee: 143 km (88 mi). Inclination: 30.94 deg. Period: 88.48 min. See TRICOM 1R (Tasuki). ..
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