RH-560

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RH-560

Part of RH

Indian sounding rocket. 2 stage vehicle derived from French Stromboli engine technology.

Status: Active. First Launch: 1974-04-24. Last Launch: 2010-03-03. Number: 19 . Thrust: 76.00 kN (17,085 lbf). Gross mass: 1,300 kg (2,800 lb). Height: 8.40 m (27.50 ft). Diameter: 0.56 m (1.83 ft). Apogee: 400 km (240 mi).

2 stage vehicle consisting of 1 x RH-560 + 1 x RH-300.

Country: India. Launch Sites: Sriharikota. Stages: RH-300 engine, RH-560 engine. Agency: ISRO.

1974 April 24 - . 13:00 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

First test - . Nation: India. Agency: ISRO. Apogee: 280 km (170 mi).

1976 October 1 - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560. FAILURE: Failure.

3-t engine test - . Nation: India. Agency: ISRO. Apogee: 100 km (60 mi).

1977? - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

TVC test - . Nation: India. Agency: ISRO. Apogee: 100 km (60 mi).

1977 February 14 - . 13:00 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

ISRO (Langmuir) Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 300 km (180 mi).

1979 June 24 - . 17:06 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

X-ray astronomy mission - . Nation: India. Agency: ISRO. Apogee: 332 km (206 mi).

1980 February 16 - . 08:50 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

Eclipse control Eclipse mission - . Nation: India. Agency: ISRO. Apogee: 330 km (200 mi).

1980 February 16 - . 10:15 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560. FAILURE: Failure.

Eclipse F-region Eclipse mission - . Nation: India. Agency: ISRO. Apogee: 0 km (0 mi).

1980 October 1 - . 15:33 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

Spread F (360 / 80) Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 350 km (210 mi).

1982 February 16 - . 13:39 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 364 km (226 mi).

1982 March 1 - . 13:35 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 364 km (226 mi).

1982 November 23 - . 15:10 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

Spread F Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 330 km (200 mi).

1982 November 29 - . 16:50 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

Spread F Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 330 km (200 mi).

1987 May 4 - . 04:40 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

SPICE-2? Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 280 km (170 mi).

1988 October 4 - . 16:00 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

ESF Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 348 km (216 mi).

1992 July 3 - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 320 km (190 mi).

1993 February 19 - . 13:15 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

Ba release Ionosphere / release mission - . Nation: India. Agency: ISRO. Apogee: 300 km (180 mi).

1993 February 19 - . 13:45 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

Ba release Ionosphere / release mission - . Nation: India. Agency: ISRO. Apogee: 290 km (180 mi).

1993 April 19 - . 05:50 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

SPICE-3 Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 323 km (200 mi).

2010 March 3 - . 03:00 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560.

ATV-DO1 Scramjet - . Nation: India. Agency: ISRO. Apogee: 46 km (28 mi).
The booster accelerated the passive scramjet to Mach 6 and sustained Mach 6 +.05 and dynamic pressure (80 + 35 kPa) for seven seconds. These conditions were required for a stable ignition of an active scramjet engine combustor module, planned in the flight of ATV-D2.

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