SS-520 - Japanese solid fuel rocket. The predecessor of the SS-520 is the geophysical rocket. The rocket is manufactured by IHI Aerospace [1]
Content
SS-520. Geophysical version
| SS-520 Geophysical Version | |
|---|---|
| General information | |
| A country | Japan |
| Family | S-520 |
| Manufacturer | IHI Corporation |
| Main characteristics | |
| Number of steps | 2 |
| Launch history | |
| condition | operated by |
| Launch locations | Japan Utinour Space Center Norway ( Svalbard ) |
| Number of starts | 2 geophysical |
| • successful | 2 geophysical |
| First start | February 5, 1998 (geophysical) |
| Last run | December 4, 2000 (geophysical) |
The geophysical two-stage version of the rocket was launched by the Institute of Space Research and Astronautics of Japan ( Eng. Institute of Space and Astronautical Science , ) for scientific research in the magnetosphere and in microgravity [2] . The rocket is manufactured by IHI Aerospace [1] .
It allows suborbital launches with a load of up to 140 kg to a height of up to 800 km [2] . The height of the rocket is 9.65 m, diameter - 0.52 m, weight - 2.6 tons. [3]
The first stage is based on the S-520 solid-fuel single-stage meteorological rocket. The motor housing is made of high-strength steel HT-140 [4] . Vertical stabilizers located in the lower part of the first stage provide missile control during flight [5] .
The second stage is made entirely of carbon fiber composite material [2] . Both stages use solid rocket fuel based on HTPB . The head fairing is made of fiberglass [5] .
The flight is stabilized by swirling along the longitudinal axis with the help of stabilizers. The stabilizers are made in the form of a three-layer sandwich of aluminum honeycombs coated with a lining of carbon and glass plastic. The leading edge of the stabilizers is made of titanium [4] .
The first launch took place from a launcher in the Utinour Space Center on February 5, 1998. The second launch took place on December 4, 2000 from the launch site of near the town of Ny-Ålesund on the Svalbard archipelago in Norway [2] .
Startup List
| No. | Date and Time ( UTC ) | Version | Launch pad | Payload | Orbit | Result |
|---|---|---|---|---|---|---|
| one | February 5, 1998, | SS-520 No. 1 | Utinour Space Center | ENA / EPS / LAP | Geophysical launch | Success |
| Reached altitude 750 km | ||||||
| 2 | December 4, 2000, | SS-520 No. 2 | Ion outflow | Geophysical launch | Success | |
| Reached an altitude of 1108 km | ||||||
SS-520. Version for orbital launches
| SS-520 | |
|---|---|
| General information | |
| A country | Japan |
| Family | SS-520 |
| Appointment | Launch vehicle |
| Developer | IHI Aerospace Co. Ltd. |
| Manufacturer | IHI Aerospace Co. Ltd. |
| Main characteristics | |
| Number of steps | 3 |
| Length (with GP) | 9.54 m |
| Diameter | 0.52 m |
| Starting weight | 2600 kg |
| Payload mass | |
| • at the DOE | > 4 kg |
| Launch history | |
| condition | test launches |
| Launch locations | Japan Utinour Space Center |
| Number of starts | 2 |
| • successful | one |
| • unsuccessful | one |
| First start | January 15, 2017 |
| Last run | February 3, 2018 |
The missile was created by adding the third stage to the SS-520 high-altitude research rocket and the corresponding refinement of the on-board systems. The third stage also uses solid rocket fuel based on HTPB .
The height of the rocket is 9.54 m, the launch weight is 2.6 tons. It can bring a payload of more than 4 kg to the DOE [6] . The thrust of the first-stage engine is 14.6 tons (145-185 kN ), the specific impulse is 265 s. The fuel mass of the first stage - 1587 kg, the second - 325, the third - 78. The orientation of the rocket after separation of the first stage is provided by the Japanese system . ラ - ラ イ ン (Ramurain) - four pulsed engines operating on compressed nitrogen. Nitrogen is stored in a 5.7 liter tank at a pressure of 230 bar [7] . The telemetry control and transmission system was created by Canon Electronics [8] . The third stage did not have a telemetry system. To determine the final parameters of the orbit, a GPS sensor was installed on it, which transmitted the signal through the Iridium system [7] .
One of the features of the launch vehicle is the widespread use of not specialized, but affordable consumer components. This is done to reduce the cost of the launch vehicle, which affects the cost of launching the payload [9] .
The first launch was funded by the Ministry of Economy, Trade and Industry; launch cost of about 400 million yen (3.5 million USD ) [10]
At the time of launches, it was the smallest launch vehicle to launch a payload into Earth orbit.
Startup List
| External video files | |
|---|---|
| Launch of SS-520 No. 4 January 14, 2017 | |
| External video files | |
|---|---|
| Launch of SS-520 No. 5 February 3, 2018 | |
| No. | Date and Time ( UTC ) | Version | Launch pad | Payload | Orbit | Result | NSSDC ID | SCN |
|---|---|---|---|---|---|---|---|---|
| one | January 14, 2017 , | SS-520 No. 4 | Utinour Space Center | TRICOM-1 [6] | DOE | Failure | ||
| The launch of the approximately 3-kilogram 3U- cubicate TRICOM-1 developed by the University of Tokyo and equipped with five cameras for taking the Earth’s surface and a communication terminal for relaying the radio signal [11] . It was planned to put the satellite into orbit with parameters 180 × 1500 km, inclination 31 ° [6] [11] [12] At the 20th second of the flight, the telemetry received from the rocket disappeared [13] [14] ; the rocket reached a peak altitude of about 190 km, after which it fell into the Pacific Ocean. The investigation showed that the most likely cause of the accident was a short circuit in the wiring: during the flight, due to temperature and vibration, the insulation of the wire passing through the aluminum case of the stage was frayed and broken. [15] [16] [17] | ||||||||
| 2 | February 3, 2018 , | SS-520 No. 5 | Utinour Space Center | (TRICOM-1R) [18] | DOE | Success | 2018-016A | 43201 |
| Due to the failure of the previous launch, the PH underwent some changes, including the protection of the wiring harness between the second and third stages. [19] Orbit 187 × 2012 km | ||||||||
Links
- Gunter Dirk Krebs. SS-520 family . Launch Vehicles . Gunter's Space Page. Date of treatment July 22, 2017. Archived July 22, 2017.
- Experimental Launch of World's Smallest Orbital Space Rocket ends in Failure . Spaceflight101 (January 14, 2017). Date of treatment July 22, 2017. Archived July 22, 2017.
- JAX commits to Minirocket Re-Flight Mission after Design Flaw Discovery . Spaceflight101 (February 14, 2017). Archived July 22, 2017.
- SS520-4 号 機 実 験 失敗 の 原因 究 明 結果 お よ び 対 策 に つ い て (Investigation Results) (Japanese) . JAXA (February 14, 2017). Archived on April 25, 2017.
- Failure of the SS520 No. 4 experiment and measures to be taken (Investigation Results ) . JAXA (February 14, 2017). Archived July 22, 2017.
- 大 貫 剛. 小型 ロ ケ ッ ト SS-520 失敗 、 原因 は 「徹底 し た 軽 量化」 (The SS-520 small missile is out of order, the reason is “careful weight loss”) (Japanese) . Sorae.jp (February 14, 2017). Date of treatment July 22, 2017. Archived July 22, 2017.
Literature
- Afanasyev I. Project of the Japanese nanocarrier // Cosmonautics News : Journal. - 2016. - September ( t. 26 , No. 9 (404) ). - S. 45 .
- Ryzhkov E. The failure of the Japanese "nano-launcher" // Cosmonautics News : Journal. - 2017. - March ( t. 27 , No. 3 (410) ). - S. 35-36 .
Notes
- ↑ 1 2 Sounding Rocket (inaccessible link) . IHI Aerospace . Archived on January 20, 2017.
- ↑ 1 2 3 4 SS-520 Institute of Space and Astronautical Science .
- ↑ Sounding Rockets . JAXA .
- ↑ 1 2 Afanasyev I, 2016 .
- ↑ 1 2 S-520 (English) . Institute of Space and Astronautical Science .
- ↑ 1 2 3 SS-520 4 号 機 実 験 の 実 施 に つ い て (Japanese) . JAXA (December 8, 2016). Archived December 8, 2016.
- ↑ 1 2 Spaceflight101, January 14, 2017 .
- ↑ Japan's space agency to try again with minirocket launch in 2017 . NIKKEI (February 3, 2017). Date of treatment July 22, 2017. Archived on February 13, 2017.
- ↑ Sergey Moroz. The accident of the Japanese launch vehicle SS-520-4 . Rocket science and astronautics . Science and Technology (January 17, 2017). Date of treatment July 23, 2017. Archived July 23, 2017.
- ↑ Ryzhkov E, 2017 , p. 36.
- ↑ 1 2 Smallest Orbital Launch Vehicle ready for Liftoff from Japan . Spaceflight101 (10 January 2017).
- ↑ JAXA SS-520 rocket set for TRICOM-1 launch to demo small rocket capability . NASA Spaceflight (January 10, 2017).
- ↑ Experimental Launch of World's Smallest Orbital Space Rocket ends in Failure . Spaceflight101 (January 14, 2017).
- ↑ Japan launched the smallest launch vehicle in the world into orbit. A rocket fell into the sea - Meduza (Russian) , Meduza . Date of treatment January 15, 2017.
- ↑ SS520-4 号 機 実 験 失敗 の 原因 究 明 結果 お よ び 対 策 に つ い て (Investigation Results) (Japanese) . JAXA (February 14, 2017). Archived on April 25, 2017.
- ↑ JAXA commits to Minirocket Re-Flight Mission after Design Flaw Discovery . Spaceflight101 (February 14, 2017).
- ↑ Japan's space agency to try again with minirocket launch in 2017 . NIKKEI (February 13, 2017).
- ↑ SS-520 5 号 機 に よ る 超 小型 衛星 打上 げ 実 証 実 験 に つ い て (Japanese) JAXA (November 13, 2017). Archived on November 13, 2017.
- ↑ SS-520 5 号 機 の 進 捗 状況 に つ い て (Japanese) . JAXA (September 5, 2017). Archived October 17, 2017.