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Jaguar RTV
Credit - via Jean-Jacques Serra
Test vehicle. Country: UK/Australia. Status: Retired 1974.

The Jaguar was designed by the RAE Supersonics Department as part of the HRV (Hypersonic Research Vehicle) program. This was a joint project with the Australian Weapons Research Establishment for testing of re-entry vehicles at high speeds. Regardless of the variant, the Rook first stage would propel the upper stages and subscale RV to a high altitude. The upper stages would then fire downward to push the RV into the atmosphere at speeds of up to 5 km/s. After the conclusion of the HRV project in April 1970, tests continued using the Jabiru 3 with other aerothermal experiments until November 1974.

Manufacturer: RAE, WRE. Launches: 28. Success Rate: 100.00%. First Launch Date: 1960-08-17. Last Launch Date: 1974-11-20. Launch data is: incomplete. Version:

Jaguar 1.

Three stage version consisting of 1 x Rook II + 1 x Gosling IIN + 1 x Lobster I

The Rook motor was 0.43 m in diameter and 5.28 m long. It contained a case-bonded charge of 846 kg of non-aluminized plastic propellant giving a total impulse of 1760 kN-seconds in 5.6 seconds; with a maximum thrust of 323 kN and a specific impulse of 213 seconds. The motor was capable of withstanding the 40g acceleration it provided during firing. It was employed as the first propulsion stage of the Leopard and Jaguar (Jabiru) supersonic test vehicles, and by itself in single-stage test applications.

Four Gosling motors with canted nozzles were used as boosters for the British Thunderbird ramjet surface-to-air missile. 664 Gosling IV motors were supplied for the Thunderbird, Bloodhound, and Seaslug Mark II missiles.

For sounding rocket applications, motors were supplied with in-line nozzles. The Gosling IV had an a all up mass of 256 kg, was 3.00 m long, and 0.254 m in diameter. It produced an average thrust of 124 kN over its 3.15 second burn time.

Launches: 10. First Launch Date: 1960-08-17. Last Launch Date: 1964-02-12. Apogee: 24 km (14 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 1,680 kg (3,700 lb). Core Diameter: 0.44 m (1.44 ft). Total Length: 11.90 m (39.00 ft).

  • Stage1: 1 x Rook II. Gross Mass: 1,057 kg (2,330 lb). Empty Mass: 186 kg (410 lb). Motor: 1 x Rook. Thrust (vac): 300.000 kN (67,440 lbf). Burn time: 5.50 sec. Length: 5.40 m (17.70 ft). Diameter: 0.44 m (1.44 ft). Propellants: Solid.
  • Stage2: 1 x Jaguar 1-2. Gross Mass: 200 kg (440 lb). Motor: 1 x Gosling. Thrust (vac): 140.000 kN (31,470 lbf). Burn time: 3.00 sec. Length: 3.50 m (11.40 ft). Diameter: 0.26 m (0.85 ft). Propellants: Solid.
  • Stage3: 1 x Jaguar 1-3. Motor: 1 x Lobster. Diameter: 0.18 m (0.59 ft). Propellants: Solid.
Version:

Jaguar 2.

Three stage version consisting of 1 x Rook IIIA + 1 x Goldfinch II + 1 x Gosling IV

The Rook motor was 0.43 m in diameter and 5.28 m long. It contained a case-bonded charge of 846 kg of non-aluminized plastic propellant giving a total impulse of 1760 kN-seconds in 5.6 seconds; with a maximum thrust of 323 kN and a specific impulse of 213 seconds. The motor was capable of withstanding the 40g acceleration it provided during firing. It was employed as the first propulsion stage of the Leopard and Jaguar (Jabiru) supersonic test vehicles, and by itself in single-stage test applications.

Four Gosling motors with canted nozzles were used as boosters for the British Thunderbird ramjet surface-to-air missile. 664 Gosling IV motors were supplied for the Thunderbird, Bloodhound, and Seaslug Mark II missiles.

For sounding rocket applications, motors were supplied with in-line nozzles. The Gosling IV had an a all up mass of 256 kg, was 3.00 m long, and 0.254 m in diameter. It produced an average thrust of 124 kN over its 3.15 second burn time.

Launches: 4. First Launch Date: 1964-10-02. Last Launch Date: 1966-11-01. Apogee: 30 km (18 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,040 kg (4,490 lb). Core Diameter: 0.44 m (1.44 ft). Total Length: 12.50 m (41.00 ft).

  • Stage1: 1 x Rook IIIA. Gross Mass: 1,057 kg (2,330 lb). Empty Mass: 186 kg (410 lb). Motor: 1 x Rook. Thrust (vac): 300.000 kN (67,440 lbf). Burn time: 5.50 sec. Length: 5.40 m (17.70 ft). Diameter: 0.44 m (1.44 ft). Propellants: Solid.
  • Stage2: 1 x Skylark 6 AC-1. Gross Mass: 400 kg (880 lb). Empty Mass: 89 kg (196 lb). Motor: 1 x Goldfinch II. Burn time: 3.50 sec. Length: 2.50 m (8.20 ft). Diameter: 0.44 m (1.44 ft). Propellants: Solid.
  • Stage3: 1 x Jabiru-3. Gross Mass: 300 kg (660 lb). Motor: 1 x Gosling. Thrust (vac): 140.000 kN (31,470 lbf). Burn time: 3.00 sec. Length: 3.50 m (11.40 ft). Diameter: 0.26 m (0.85 ft). Propellants: Solid.
Version:

Jabiru 2.

The Rook motor was 0.43 m in diameter and 5.28 m long. It contained a case-bonded charge of 846 kg of non-aluminized plastic propellant giving a total impulse of 1760 kN-seconds in 5.6 seconds; with a maximum thrust of 323 kN and a specific impulse of 213 seconds. The motor was capable of withstanding the 40g acceleration it provided during firing. It was employed as the first propulsion stage of the Leopard and Jaguar (Jabiru) supersonic test vehicles, and by itself in single-stage test applications.

Launches: 7. First Launch Date: 1967-12-07. Last Launch Date: 1970-04-01. Apogee: 30 km (18 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,000 kg (4,400 lb). Core Diameter: 0.44 m (1.44 ft). Total Length: 12.50 m (41.00 ft).

  • Stage1: 1 x Rook IIIA. Gross Mass: 1,057 kg (2,330 lb). Empty Mass: 186 kg (410 lb). Motor: 1 x Rook. Thrust (vac): 300.000 kN (67,440 lbf). Burn time: 5.50 sec. Length: 5.40 m (17.70 ft). Diameter: 0.44 m (1.44 ft). Propellants: Solid.
  • Stage2: 1 x Skylark 6 AC-1. Gross Mass: 400 kg (880 lb). Empty Mass: 89 kg (196 lb). Motor: 1 x Goldfinch II. Burn time: 3.50 sec. Length: 2.50 m (8.20 ft). Diameter: 0.44 m (1.44 ft). Propellants: Solid.
  • Stage3: 1 x Jabiru-3. Gross Mass: 300 kg (660 lb). Motor: 1 x Gosling. Thrust (vac): 140.000 kN (31,470 lbf). Burn time: 3.00 sec. Length: 3.50 m (11.40 ft). Diameter: 0.26 m (0.85 ft). Propellants: Solid.
Version:

Jabiru 3.

Two stage version consisting of 1 x Rook IIIA + 1 x Rook IIIB

The Rook motor was 0.43 m in diameter and 5.28 m long. It contained a case-bonded charge of 846 kg of non-aluminized plastic propellant giving a total impulse of 1760 kN-seconds in 5.6 seconds; with a maximum thrust of 323 kN and a specific impulse of 213 seconds. The motor was capable of withstanding the 40g acceleration it provided during firing. It was employed as the first propulsion stage of the Leopard and Jaguar (Jabiru) supersonic test vehicles, and by itself in single-stage test applications.

Launches: 7. First Launch Date: 1971-10-20. Last Launch Date: 1974-11-20. Apogee: 30 km (18 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,000 kg (4,400 lb). Core Diameter: 0.44 m (1.44 ft). Total Length: 12.70 m (41.60 ft).

  • Stage1: 1 x Rook IIIA. Gross Mass: 1,057 kg (2,330 lb). Empty Mass: 186 kg (410 lb). Motor: 1 x Rook. Thrust (vac): 300.000 kN (67,440 lbf). Burn time: 5.50 sec. Length: 5.40 m (17.70 ft). Diameter: 0.44 m (1.44 ft). Propellants: Solid.
  • Stage2: 1 x Rook IIIB. Gross Mass: 1,057 kg (2,330 lb). Empty Mass: 186 kg (410 lb). Motor: 1 x Rook. Thrust (vac): 300.000 kN (67,440 lbf). Burn time: 5.50 sec. Length: 5.40 m (17.70 ft). Diameter: 0.44 m (1.44 ft). Propellants: Solid.
Jaguar Chronology

1960 August 17 - Aberporth -. Jaguar 1 G1 Test mission Agency: RAE. Apogee: 20 km (12 mi).

1960 December 15 - Woomera LA2. Jaguar 1 J1 Test mission Agency: RAE. Apogee: 24 km (14 mi).

1961 April 21 - Woomera LA2. Jaguar 1 J2 Test mission Agency: RAE. Apogee: 24 km (14 mi).

1961 July 26 - Woomera LA2. Jaguar 1 J3 Test mission Agency: RAE. Apogee: 24 km (14 mi).

1961 November 1 - Woomera LA2. Jaguar 1 J4 Test mission Agency: RAE. Apogee: 24 km (14 mi).

1962 April 4 - Woomera LA2. Jaguar 1 J5 Test mission Agency: RAE. Apogee: 24 km (14 mi).

1962 June 26 - Woomera LA2. Jaguar 1 J6 Test mission Agency: RAE. Apogee: 24 km (14 mi).

1962 August 1 - Woomera LA2. Jaguar 1 J7 Test mission Agency: RAE. Apogee: 24 km (14 mi).

1963 March 27 - Woomera LA2. Jaguar 1 J8 Test mission Agency: RAE. Apogee: 24 km (14 mi).

1964 February 12 - Woomera LA2. Jaguar 1 J9 Test mission Agency: RAE. Apogee: 24 km (14 mi).

1964 October 2 - Woomera LA2. Jaguar 2 J201 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1965 August 25 - Woomera LA2. Jaguar 2 J202 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1966 August 10 - Woomera LA2. Test mission Agency: RAE. Apogee: 30 km (18 mi).

1966 November 1 - Woomera LA2. Jaguar 2 J204 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1967 December 7 - Woomera LA2. Jabiru 2 J205 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1968 July 18 - Woomera LA2. Jabiru 2 J206 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1969 April 1 - Woomera LA2. Jabiru 2 J207 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1969 May 1 - Woomera LA2. Jabiru 2 J202-2 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1969 July 16 - Woomera LA2. Jabiru 2 J208 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1969 October 16 - Woomera LA2. Jabiru 2 J209 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1970 April 1 - Woomera LA2. Jabiru 2 J210 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1971 October 20 - Woomera LA2. Jabiru 3 J-1 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1971 December 4 - Woomera LA2. Jabiru 3 J-2 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1973 November 14 - Woomera LA2. Jabiru 3 J-3 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1973 December 6 - Woomera LA2. Jabiru 3 J-4 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1974 September 6 - Woomera LA2. Jabiru 3 J-5 Jabiru II test Agency: RAE. Apogee: 30 km (18 mi).

1974 October 31 - Woomera LA2. Jabiru 3 J-6 Test mission Agency: RAE. Apogee: 30 km (18 mi).

1974 November 20 - Woomera LA2. Jabiru 3 J-7 Test mission Agency: RAE. Apogee: 30 km (18 mi).

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