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INTA-300
Sounding rocket. Country: Spain. Status: Retired 1994.

The Instituto Nacional de Tecnica Aerospacial was tasked in 1967 to develop Spain's first sounding rocket. INTA contracted with British Aerojet to provide the necessary technical expertise and designed a rocket built from existing British solid motors. This was followed by versions using Spanish-manufactured versions of British motors. The stop-and-go program extended over nearly 30 years.

Manufacturer: INTA. Launches: 9. Failures: 1. Success Rate: 88.89%. First Launch Date: 1969-07-19. Last Launch Date: 1994-04-16. Launch data is: complete. Version:

INTA-255.

Vehicle consisting of 4 x Chick + 1 x Goose. All motors ignited simultaneously at lift-off, the Chicks burning for 0.2 seconds, while the Goose continued for 17 seconds.

The requirement was to boost a 15 kg payload up to 150 km. The technology acquired during the development and brief firing program led to the more ambitious INTA-300.

Launches: 3. First Launch Date: 1969-07-19. Last Launch Date: 1970-12-22. Apogee: 150 km (90 mi). Liftoff Thrust: 42.000 kN (9,441 lbf). Total Mass: 340 kg (740 lb). Core Diameter: 0.26 m (0.85 ft). Total Length: 6.03 m (19.78 ft).

  • Stage0: 4 x INTA-255-0. Empty Mass: 6.00 kg (13.20 lb). Motor: 1 x Chick. Thrust (vac): 20.000 kN (4,496 lbf). Burn time: 0.20 sec. Length: 0.60 m (1.96 ft). Diameter: 0.10 m (0.32 ft). Propellants: Solid.
  • Stage1: 1 x INTA-255-1. Gross Mass: 300 kg (660 lb). Empty Mass: 95 kg (209 lb). Motor: 1 x Goose II. Thrust (vac): 22.000 kN (4,945 lbf). Burn time: 17 sec. Length: 3.40 m (11.10 ft). Diameter: 0.26 m (0.85 ft). Propellants: Solid.
Version:

INTA-300. Popular Name: Flamenco.

Two stage vehicle consisting of 1 x Heron + 1 x Snipe

In 1968 Spain's Nactional Space Plan proclaimed the requirement for an indigenous sounding rocket that could carry a 50 kg payload to 300 km. Following initial experience with the INTA-255, British Aerojet assisted the Instituto Nacional de Tecnica Aerospacial in development of this larger rocket. The Aneto first stage burned for 3 seconds, followed by the Teide second stage generating 16.3 kN over a 16 second burn time. Stabilisation was by four small spin motors at the tips of the fins. Development proceeded at a slow rate during the 1970's, culminating in a fully successful launch in 1981. But at that point funding for the project was cut off.

Funds again became available nearly a decade later. Three sets of motors remained in storage, and one set was test-fired to verify their safety. Two final launches were made with the remaining motors. These modified rockets, with heavier and wider payloads, were designated INTA-300B.

Launches: 4. Failures: 1. First Launch Date: 1974-10-09. Last Launch Date: 1981-02-18. Apogee: 250 km (150 mi). Liftoff Thrust: 138.000 kN (31,023 lbf). Total Mass: 503 kg (1,108 lb). Core Diameter: 0.26 m (0.85 ft). Total Length: 7.27 m (23.85 ft).

  • Stage1: 1 x INTA-300-1. Gross Mass: 300 kg (660 lb). Empty Mass: 72 kg (158 lb). Motor: 1 x Gosling 4. Thrust (vac): 137.000 kN (30,798 lbf). Burn time: 3.10 sec. Length: 3.60 m (11.80 ft). Diameter: 0.26 m (0.85 ft). Propellants: Solid.
  • Stage2: 1 x Fulmar-2. Gross Mass: 200 kg (440 lb). Empty Mass: 58 kg (127 lb). Motor: 1 x Snipe. Thrust (vac): 16.000 kN (3,596 lbf). Burn time: 16 sec. Length: 2.10 m (6.80 ft). Diameter: 0.26 m (0.85 ft). Propellants: Solid.
Version:

INTA-300B.

Later version for heavier payloads fired in 1993-1994.

Launches: 2. First Launch Date: 1993-10-21. Last Launch Date: 1994-04-16. Apogee: 250 km (150 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 500 kg (1,100 lb). Core Diameter: 0.26 m (0.85 ft). Total Length: 7.30 m (23.90 ft).

  • Stage1: 1 x INTA-300-1. Gross Mass: 300 kg (660 lb). Empty Mass: 72 kg (158 lb). Motor: 1 x Gosling 4. Thrust (vac): 137.000 kN (30,798 lbf). Burn time: 3.10 sec. Length: 3.60 m (11.80 ft). Diameter: 0.26 m (0.85 ft). Propellants: Solid.
  • Stage2: 1 x Fulmar-2. Gross Mass: 200 kg (440 lb). Empty Mass: 58 kg (127 lb). Motor: 1 x Snipe. Thrust (vac): 16.000 kN (3,596 lbf). Burn time: 16 sec. Length: 2.10 m (6.80 ft). Diameter: 0.26 m (0.85 ft). Propellants: Solid.
INTA Chronology

1969 July 19 - El Arenosillo -. INTA-255 1 Booster test Agency: INTA. Apogee: 1.00 km (0.60 mi).

1969 December 20 - El Arenosillo -. INTA-255 2 Test mission Agency: INTA. Apogee: 73 km (45 mi).

1970 December 22 - El Arenosillo -. INTA-255 3 Test mission Agency: INTA. Apogee: 132 km (82 mi).

1974 October 9 - 04:49 GMT - El Arenosillo -. INTA-300 F-74001 Test mission Agency: FRG. Apogee: 254 km (157 mi). Failed to reach expected altitude.

1975 October 21 - 11:42 GMT - El Arenosillo -. INTA-300 F-75001 Aeronomy / test Agency: FRG. Apogee: 240 km (140 mi). Failed to reach expected altitude.

1978 June 28 - El Arenosillo -. FAILURE: Failure. Aeronomy mission Agency: INTA. Apogee: 0 km ( mi).

1981 February 18 - El Arenosillo -. Aeronomy mission Agency: INTA. Apogee: 285 km (177 mi). First completely successful launch.

1993 October 21 - 01:46 GMT - El Arenosillo -. INTA-300B IAA FEIROX / FEIROH Aeronomy mission Agency: INTA. Apogee: 154 km (95 mi).

1994 April 16 - 01:22 GMT - El Arenosillo -. INTA-300B IAA O2-INTA300 Aeronomy mission Agency: INTA. Apogee: 156 km (96 mi).

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