KVD-1
| Country of origin | USSR/Russia |
|---|---|
| First flight | 2001-04-20, GSAT-1 Mission, GSLV debut flight |
| Last flight | 2010-12-25, GSAT-5P launch, GSLV Mk I final flight |
| Designer | KB KhIMMASH |
| Application | Upper stage engine |
| Associated L/V | GSLV Mk 1 |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | Liquid oxygen / Liquid hydrogen |
| Mixture ratio | 6 |
| Cycle | Staged combustion |
| Configuration | |
| Chamber | 1 + 2 verniers |
| Performance | |
| Thrust (vac.) | 69.6 kN (15,600 lbf) |
| Chamber pressure | 5.6 MPa (810 psi) |
| Isp (vac.) | 462s |
| Burn time | 800s (600s in a single burn) |
| Gimbal range | None; uses 2 vernier engines for attitude control[1] |
| Dimensions | |
| Length | 2.14 m (7 ft 0 in) |
| Diameter | 1.58 m (5 ft 2 in) |
| Dry weight | 282 kg (622 lb) |
| References | |
| References | [2][3][4] |
KVD-1 was an upper stage LOX/LH2 cryogenic engine developed by Isayev Design Bureau (now KB KhIMMASH) of Russia in early 1960s. It is a modified version of RD-56 which was developed with an intention to manufacture cryogenic engine for upper stage of Lunar N-1 launch vehicle. It was to be used in USSR moon missions.[5] KVD-1 can produce engine thrust of 7.5 tonnes.
Initial Development
KVD-1 was originated from the RD-56 engine which were intended to be used for USSR moon programmes.[6] RD-56 aka 11D56 engines were developed for N1M rocket programme, the planned derivative of N1, but later they were abandoned due to four successive launch failures of N1.[7] Later the design of the engine was sold to ISRO under the name "KVD-1" under a deal worth $120 million [8] with soviet agency Glavkosmos which enabled ISRO to import 2 KVD-1 engines and an agreement for transfer of technology from Russia.[9]
ISRO Programme
The engines were proved to be inefficient because of low thrust/weight ratio. Later Russian agency optimised the engine to launch a satellite with liftoff mass of 2.5 tonnes. As a result, INSAT-4CR satellite with a liftoff mass of 2,140 kg was launched in 2007.[7]
Sanctions imposed by United States
In 1991, An agreement was signed between India and Russia for technology transfer to India so that KVD-1 engines can be built indigenously in India. But later in July 1993, US imposed sanctions on ISRO and Glavkosmos saying it voids the Missile Technology Control Regime. After suffering setback in this case ISRO was forced to develop its own cryogenic programme.[10]
Features
The engine was single chamber fueled rocket which could be used as cryogenic engines for launching of spacecrafts that could be put in elliptical and geostationary orbits.
- Unfuelled mass : 282 kg (621 lb).
- Height : 2.14 m
- Diameter : 1.56 m
- Specific impulse: 462 seconds
- Thrust: 69.60 kN (15,647 lbf)
- Burn time : 800 seconds[2]
Use
KVD-1 was used in following launch vehicles
- GSLV Mk I
References
- ↑ Brügge, Norbert. "Geosynchronous Satellite Launch Vehicle (GSLV)". B14643.de. Retrieved 2015-06-01.
- 1 2 Wade, Mark. "RD-56". astronautix.com. Encyclopedia Astronautica. Retrieved 2014-01-07.
- ↑ "Двигатель КВД1. Кислородно-водородный блок 12КРБ" [Engine KVD-1. Hydrogen Oxygen unit 12KRB]. kbhmisaeva.ru (in Russian). KB KhIMMASH. Retrieved 2015-08-03.
- ↑ "KVD-1 & S5.92 Brochure" (PDF). KB KhIMMASH. 1998-10-13. Retrieved 2015-08-03.
- ↑ Simha, Rakesh Krishnan (December 4, 2013). "How India's cryogenic programme was wrecked". indrus.in. Retrieved January 7, 2014.
- ↑ V. Rachuk , and N. Titk ov. "The First Russian LOX-LH 2 Expander Cycle LRE: RD0146" (PDF). LPRE Germany. p. 15. Retrieved January 7, 2014.
- 1 2 "The long road to cryogenic technology". The Hindu. Chennai. April 21, 2011. Retrieved January 7, 2014.
- ↑ "Cryogenic Upper Stage (CUS)". justthe80.com. Retrieved January 7, 2014.
- ↑ "ISRO Cryogenic Engine: Cryogenic Upper Stage (CUS) , Videos and Report". Anant. defence.pk. Mar 30, 2013. Retrieved January 7, 2014.
- ↑ Laxman, Srinivas (Jan 6, 2014). "India overcame US sanctions to develop cryogenic engine". Times of India. Retrieved January 22, 2014.
