Rohini is a series of sounding rockets developed by the Indian Space Research Organisation (ISRO) for meteorological and atmospheric study. These sounding rockets are capable of carrying payloads of 2 to 200 kilograms (4.4 to 440.9 lb) between altitudes of 100 to 500 kilometres (62 to 311 mi). The ISRO currently uses RH-200, RH-300, RH-300 Mk-II and RH-560 Mk-II rockets, which are launched from the Thumba Equatorial Rocket Launching Station (TERLS) in Thumba and the Satish Dhawan Space Center in Sriharikota.
Nomenclature :
The rockets in the series are designated with the letters RH (for “Rohini”), followed by a number corresponding to the diameter (in millimetres) of the rocket.
Series :
RH-75 :
The RH-75, the first sounding rocket developed by India, was launched from TERLS on November 20, 1967. It weighed 32 kilograms (71 lb), had a diameter of 75 millimetres (3.0 in) and flew 15 times between November 1967 and September 1968.
RH-125 :
This rocket was launched on October 9, 1971 from Sriharikota. It was a two-stage rocket using a solid propellant, carrying a 7 kilograms (15 lb) payload to 19 kilometres (12 mi) in altitude. It flew twice between January 1970 and October 1971.
RH-200 :
The RH-200 has a maximum launch altitude of 70 kilometres (43 mi).
RH-300 :
The Rh-300 is a single stage sounding rocket, derived from French Belier rocket engine technology. It has a launch altitude of 100 km (62 mi). A variant, the RH-300 Mk-II, has a maximum launch altitude of 116 kilometres (72 mi).
RH-560 :
This two stage vehicle is derived from French Stromboli engine technology. Another variant, the RH-560 Mk-II, can reach a maximum launch altitude of 548 kilometres (341 mi).
Applications :
The RH-200 is used for meteorological studies, the RH-300 Mk-II for upper-atmospheric studies and the RH-560 Mk-II for ionospheric studies. The RH-200 was used as the rocket for the first payload launch in India made by students of VIT University in Vellore.
Rohini series of sounding rockets
| Name | RH 75 | RH 125 | RH 200/125 | RH-300 | RH-300 Mk II | RH-300/200/200 | RH-560/300 | RH-560/300 Mk II |
|---|---|---|---|---|---|---|---|---|
| Gross mass | 8 kg (18 lb) | 40 kg (88 lb) | 100 kg (220 lb) | 300 kg (660 lb) | 500 kg (1,100 lb) | 500 kg (1,100 lb) | 1,300 kg (2,800 lb) | 1,600 kg (3,530 lb) |
| Height | 1.50 m (4.90 ft) | 2.50 m (8.20 ft) | 3.60 m (11.80 ft) | 4.10 m (13.40 ft) | 5.90 m (19.30 ft) | 8.00 m (26.20 ft) | 8.40 m (27.50 ft) | 9.10 m (29.80 ft) |
| Diameter | 0.0800 m (0.2620 ft) | 0.12 m (0.39 ft) | 0.20 m (0.65 ft) | 0.31 m (1.01 ft) | 0.31 m (1.01 ft) | 0.31 m (1.01 ft) | 0.56 m (1.83 ft) | 0.56 m (1.83 ft) |
| Thrust | 8.00 kN (1,798 lbf) | 17.00 kN (3,821 lbf) | 38.00 kN (8,542 lbf) | 39.00 kN (8,767 lbf) | 38.00 kN (8,542 lbf) | 76.00 kN (17,085 lbf) | 76.00 kN (17,085 lbf) | |
| Apogee | 10 kilometres (6.2 mi) | 20 kilometres (12 mi) | 80 kilometres (50 mi) | 100 kilometres (62 mi) | 150 kilometres (93 mi) | 300 kilometres (190 mi) | 400 kilometres (250 mi) | 500 kilometres (310 mi) |
| Stages | 1 | 1 | 2 | 1 | 1 | 3 | 2 | 2 |
| First Launch | 20 November 1967 | 1 January 1970 | 1 January 1979 | 8 June 1987 | 1 November 1985 | 24 April 1974 | 16 August 1995 | |
| Payload (kg) | 1 | 7 | 10 | 60 | 70 | 100 |
references : wikipedia
INDIAN SPACE RESEARCH ORGANISATION 