Engineering:Soyuz-5 (rocket)
| Function | Orbital Launch Vehicle |
|---|---|
| Manufacturer | RKK Energia JSC SRC Progress |
| Country of origin | Russia |
| Project cost | 61.2 ₽ billion |
| Size | |
| Height | 61.9 m (203 ft) (unmanned) 65.9 m (216 ft) (manned) |
| Diameter | 4.1 m (13 ft) |
| Mass | 530,000 kg (1,170,000 lb) |
| Stages | 3 |
| Capacity | |
| Payload to LEO | 18,000 kg (unmanned) 15,500 kg (manned) |
| Payload to GTO | 5,000 kg (11,000 lb) |
| Associated rockets | |
| Comparable | Zenit-2, Proton-M, Falcon 9, Atlas V 541, Ariane 5 ES, H-IIB, Long March 5 |
| Launch history | |
| Status | Proposal |
| Launch sites | Baikonur Baiterek |
| First stage | |
| Length | 37.14 m (121.9 ft) |
| Diameter | 4.1 m (13 ft) |
| Empty mass | 27,700 kg (61,100 lb) |
| Propellant mass | 363,000 kg (800,000 lb) |
| Engines | RD-171M |
| Thrust | 7,257 kN (1,631,000 lbf) |
| Specific impulse | 309 seconds (3.03 km/s) |
| Fuel | RG-1/LOX |
| Second stage | |
| Length | 7.77 m (25.5 ft) |
| Diameter | 4.1 m (13 ft) |
| Empty mass | 5,900 kg (13,000 lb) |
| Propellant mass | 59,000 kg (130,000 lb) |
| Engines | 2 × RD-0124A |
| Thrust | 294.3 kN (66,200 lbf) |
| Specific impulse | 359 seconds (3.52 km/s) |
| Fuel | RG-1/LOX |
| Third stage – Blok DM-03 (optional) | |
| Length | 6.28 m (20.6 ft) |
| Diameter | 3.7 m (12 ft) |
| Propellant mass | 18,700 kg (41,200 lb) |
| Engines | RD-58MF |
| Thrust | 49.03 kN (11,020 lbf) |
| Specific impulse | 372 seconds (3.65 km/s) |
| Fuel | RG-1/LOX |
Soyuz-5 (Russian: Союз-5), codenamed Fenix in Russian and Sunkar in Kazakh, is a planned Russian rocket that would be developed by JSC SRC Progress within the Project Feniks (Russian: Феникс, lit. 'Phoenix'). Initially it will replace the capability of Zenit-2, and Proton Medium, and in the future will serve as the base of a super heavy-lift launch vehicle rocket to revive the Energia/Buran capabilities. It is expected to launch from the Baikonur Baiterek, the ex Zenit-2 launch site, in a partnership with the government of Kazakhstan, with a planned debut of 2024.[1][2][3][4]
Project Organization
The current proposal is led by JSC SRC Progress, with support by Khrunichev and Makeyev, additionally, RSC Energia would handle the launch site, and supply the Blok DM-03, while Roscosmos would finance the development through the Project Fenicks under the 2016-2025 Russian space master plan. KazCosmos would also be a partner since the initial launch pad would be at Baikonur Cosmodrome Site 45 in Kazakhstan, within the framework of the Baiterek bi-national joint venture, and International Launch Services (ILS) would commercialize its services for the international market.[2][4]
The initial application of the launch vehicle would be to cover the under 5 t (5.5 tons) to GTO commercial launch segment. With the loss of the Zenit-3SLB due to Russia conflicts with Ukraine, both the decision not to develop Angara A3 and launch Angara A5 from Vostochny, the Baiterek project was without a launch vehicle. The 2016 announcement of the Proton Medium and Light, meant that ILS, would enter the medium GTO launch market. But since the Kazakh government desired to deprecate the use of highly toxic hypergolic propellants used by Proton, they would need a replacement.[2][4]
For this commercial application JSC SRC Progress proposed the Soyuz-5 in early 2016. It would start with this commercial application with the prospect of also enabling a super heavy launcher with a 80 t (88 tons) payload capability to low Earth orbit.[2][4] The Kazakh side agreed on the general terms, but the investment share was left to decide. As part of the 2016 arrangements, the Kazakh government would get ownership of one the Proton launch pads, and participate in the operations of Proton-Medium and Proton-Light. Then, they would get to participate in the Soyuz-5 launchers since its expected debut in 2024.[3][4]
Vehicle Description
Soyuz-5, as proposed in 2016, reuses many available propulsion and tooling, while enabling a platform that would replace the lost capabilities of the Zenit family, replace the Proton Light/Medium, and could serve as the boosters of a new super heavy rocket. It will initially be a two-stage rocket, but could be enhanced with an optional Blok DM-03 for geostationary missions. It would be compatible with most of the Zenit's ground infrastructure, and even use the Site 45 at Baikonur.[4]
Its tanks would be 4.1 m (13 ft) in diameter, which would enable the re use of Proton's tooling. Since they would be wider than Zenit (3.9 m (13 ft)) it would enable a higher propellant load for the same height. While this diameter enables a heavier rocket and is already compatible with train transport to Baikonur, it would prevent that cheap method for Vostochny Cosmodrome. It would use the relatively environmental friendly RG-1/LOX propellant, which would be an improvement over the highly toxic hypergolics of Proton. This has been a requirement from the Kazakh government for new projects.[2][4]
The first stage would be powered by an RD-171M (same as modern Zenit), with the option of developing a version with a 10% thrust increase, or the use of two RD-180. With a height of 37.14 m (121.9 ft) it would be higher than Zenit's first stage (32.94 m (108.1 ft)) and wider, and thus it could carry 363 t (400 tons) of propellant versus 290 t (320 tons). Its base would still feature a 3.68 m (12.1 ft) aft section for compatibility with Zeni't pad and support infrastructure.[2][4][5]
Its second stage would measure 7.77 m (25.5 ft) by 4.1 m (13 ft) in diameter, with a dry mass of 5.9 t (6.5 tons) and an RG-1/LOX load of 59 t (65 tons). It would be powered by two RD-0124A, same as Angara. But instead of arranging the four nozzles in a square, it would feature a semicircle arrangement, so the two engines would feature the eight total nozzles close to its perimeter, forming a circle. This arrangement would minimize the stage length, while keeping the engines excellent specific impulse.[2][4][5]
With a gross mass of 484 t (534 tons) against Zenit 430 t (470 tons), and the improved efficiency of its second stage, it could launch 16 t (18 tons) to a 200 km circular orbit with an inclination of 51.6° to the Equator from Baikonur. This is a significant improvement over Zenit, that could do roughly 12 t (13 tons) to the same orbit.[2][4][5][6]
For geostationary launch missions, it could optionally be equipped with a Blok DM-03 third stage. Since it would use the same propellant and is already used on the Zenit-3SL and Angara A5, it would be a low risk option.[2][4] The expected performance of 4.5 t (5.0 tons) to GTO and 2.3 t (2.5 tons) to GSO, it would improve over Zenit-3SLB 3.6 t (4.0 tons) and 1.59 t (1.75 tons).[4][7][5]
Soyuz-5 Super Heavy
Its first stage could be used as the boosters (and even core) of a super heavy rocket capable of launching 73 t (80 tons) to low Earth orbit from Baikonur or Vostochny. Improving the performance to 120 t (130 tons) and even 160 t (180 tons) was considered possible with this architecture. While the current 2016-2025 plan for deep space exploration calls for the use of the heavy Angara 5V, it would just enable 36 t (40 tons), requiring up to four launches for a single Moon mission. And would also require the use of expensive hydrogen as fuel. The Soyuz-5 Super Heavy would simplify the mission while using readily available modules.[1][4][5][6]
See also
References
- ↑ 1.0 1.1 ""Роскосмос" создаст новую сверхтяжелую ракету". Izvestia. 2016-08-22. http://izvestia.ru/news/628028. Retrieved 2016-09-16.
- ↑ 2.0 2.1 2.2 2.3 2.4 2.5 2.6 2.7 2.8 "Российско-казахстанскую ракету «Сункар» построят в Самаре к 2024 году". Izvestia. 2016-08-25. http://izvestia.ru/news/628767. Retrieved 2016-09-16.
- ↑ 3.0 3.1 "Россия передаст Казахстану пусковой комплекс для ракет "Протон"". Izvestia. 2016-08-22. http://izvestia.ru/news/632286. Retrieved 2016-09-16.
- ↑ 4.00 4.01 4.02 4.03 4.04 4.05 4.06 4.07 4.08 4.09 4.10 4.11 4.12 Zak, Anatoly (2017-11-13). "Russia charts new path to super rocket". RussianSpaceWeb. http://www.russianspaceweb.com/sunkar.html. Retrieved 2018-02-26.
- ↑ 5.0 5.1 5.2 5.3 5.4 Zak, Anatoly (2018-02-16). "Russia's "new" next manned rocket detailed". RussianSpaceWeb. http://www.russianspaceweb.com/soyuz5-lv-ptk.html. Retrieved 2018-02-26.
- ↑ 6.0 6.1 Zak, Anatoly (2018-02-16). "Preliminary design for Soyuz-5 races to completion". RussianSpaceWeb. http://www.russianspaceweb.com/soyuz5-lv-2017.html. Retrieved 2018-02-26.
- ↑ Land Launch User's Guide. Space International Services. 2014-10-01. p. 43. http://www.landlaunch.ru/download/llug_eng.pdf. Retrieved 2016-09-16.
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