Engineering:Sputnik (rocket)

Short description: Small carrier rocket

For the Sputnik 11A59 rocket, see Polyot (rocket). For other uses, see Sputnik (disambiguation).

Sputnik 727

Sputnik rocket
Function	Early (first) carrier rocket
Manufacturer	OKB-1
Country of origin	USSR
Size
Height	8K71PS: 30.0 m (98.4 ft) 8A91: 31.1 m (102 ft)
Diameter	2.99 m (9.8 ft)
Mass	267,000 kg (589,000 lb) 8A91: 269,300 kg (593,700 lb)
Stages	2
Capacity
Payload to LEO (8K71PS)	8K71PS: 500 kg (1,100 lb) 8A91: 1,327 kg (2,926 lb)
Associated rockets
Family	R-7
Comparable	Vanguard Juno I
Launch history
Status	Retired
Launch sites	LC-1/5, Baikonur
Total launches	4 (2 8K71PS, 2 8A91)
Successes	3
Failures	1 (8A91)
First flight	8K71PS: 4 October 1957 8A91: 27 April 1958
Last flight	8K71PS: 3 November 1957 8A91: 15 May 1958
Notable payloads	Sputnik 1 Sputnik 2 Sputnik 3
Boosters (Block B, V, G, D)
No. boosters	4
Engines	1 RD-107
Thrust	970 kN (220,000 lbf)
Specific impulse	306 s
Burn time	120 s
Fuel	LOX/Kerosene
First stage (Block A)
Engines	1 RD-108
Thrust	912 kN (205,000 lbf)
Specific impulse	308 s
Burn time	330 s
Fuel	LOX/Kerosene

The Sputnik rocket was an uncrewed orbital carrier rocket designed by Sergei Korolev in the Soviet Union, derived from the R-7 Semyorka ICBM. On 4 October 1957, it was used to perform the world's first satellite launch, placing Sputnik 1 into a low Earth orbit.

Two versions of the Sputnik were built, the Sputnik-PS (GRAU index 8K71PS), which was used to launch Sputnik 1 and later Sputnik 2, and the Sputnik (8A91), which failed to launch a satellite in April 1958, and subsequently launched Sputnik 3 on 15 May 1958.

A later member of the R-7 family, the Polyot, used the same configuration as the Sputnik rocket, but was constructed from Voskhod components. Because of the similarity, the Polyot was sometimes known as the Sputnik 11A59.

Specifications

• First Stage: Block B, V, G, D (four strap-on boosters)
  • Gross mass: 43.0 tons
  • Empty mass: 3.400 tons
  • Thrust (vac): 4 × 99,000 kgf = 396 Mgf (3.89 MN)
  • Isp: 306 s (3,000 N·s/kg)
  • Burn time: 120 s (2 min)
  • Isp (sl): 250 s (2,450 N·s/kg)
  • Diameter: 2.68 metres (8.8 ft)
  • Span: 2.68 metres (8.8 ft)
  • Length: 19.2 metres (63 ft) (without nozzles)
  • Propellants: LOX/Kerosene
  • Engines: 1 x RD-107-8D74PS per booster = 4
• Second Stage: Block A (core stage)
  • Gross mass: 94.0 tons
  • Empty mass: 7.495 tons
  • Thrust (vac): 99,000 kgf (970 kN)
  • Isp: 308 s (3,020 N·s/kg)
  • Burn time: 310 s (5 min 10 s)
  • Isp (sl): 241 s (2,360 N·s/kg)
  • Diameter: 2.95 metres (9.7 ft)
  • Span: 2.95 metres (9.7 ft)
  • Length: 28 metres (92 ft)
  • Propellants: LOX/Kerosene
  • Engine: 1 x RD-108-8D75PS
• Total mass: 267 tons (589,000 lb)
• Total span: 10.303 metres (33.80 ft)
• LEO payload: 500 kg
• Total liftoff thrust: 3.89 MN

Some R-7 variants

Sputnik 8A91

The Sputnik 8A91 had more powerful 8D76 and 8D77 engines installed, increasing its payload capacity, and allowing it to launch much heavier satellites than Sputnik 1 and Sputnik 2. It was launched two times, in 1958. The first launch, on 27 April, failed due to vibrations that unexpectedly occurred during the flight along the longitudinal axis of the rocket. On 15 May, it successfully launched Sputnik 3.

Sputnik specifications

• Stage number: 0 - Strap-on boosters; 4 x Sputnik 8A91-0
  • Gross mass: 43.0 tons
  • Empty mass: 3.400 tons
  • Thrust (vac): 4 × 99,000 kgf = 396 Mgf (3.89 MN)
  • Isp: 310 s (3,040 N·s/kg)
  • Burn time: 130 s (2 min 10 s)
  • Isp (sl): 252 s (2,470 N·s/kg)
  • Diameter: 2.68 metres (8.8 ft)
  • Span: 2.68 metres (8.8 ft)
  • Length: 19.2 metres (63 ft) (without nozzles)
  • Propellants: LOX/Kerosene
  • Engines: 1 x RD-107-8D76 per booster (4 total)
• Stage number: 1 - Core stage; 1 x Sputnik 8A91-1
  • Gross mass: 95.0 tons
  • Empty mass: 7.100 tons
  • Thrust (vac): 82,000 kgf (804 kN)
  • Isp: 315 s (3,090 N·s/kg)
  • Burn time: 360 s (6 min)
  • Isp (sl): 246 s (2,410 N·s/kg)
  • Diameter: 2.95 metres (9.7 ft)
  • Length:28 metres (92 ft)
  • Propellants: LOX/Kerosene
  • Engine: 1 x RD-108-8D77
• Total mass: 269.3 tons (593,700 lb)
• Total span: 10.303 metres (33.80 ft)
• LEO payload: 1,327 kg (2,925 lb)
• Total liftoff thrust: 385,950 kgf (3.784 MN, 850,870 lbf)