Rigel was begun by the US Navy in 1946. The aim was to produce a solid-rocket boosted, twin-ramjet powered, ship-launched supersonic cruise missile to attack shore targets at a range of 930 km (500 nm). Work began with simple single-ramjet test vehicles. Flights of twin-ramjet test vehicles began in May 1950. After repeated test launch failures, and success of the less ambitious Regulus subsonic cruise missile, Rigel was cancelled in August 1953.
Production missiles would have been equipped with two wingtip-mounted Marquardt 71 cm (28 in) ramjets and four solid rocket boosters. A CEP of 550 m was planned using a modified LORAN guidance system, requiring two submarines with radio beacons to be deployed along the missile's path. The Regulus II, which began development two months before Rigel was cancelled, was supersonic using proven turbojet technology, and equipped with autonomous inertial navigation.
Development Cost $: 38.000 million in 1948 dollars. Standard warhead: 1,360 kg (2,990 lb). Maximum range: 890 km (550 mi). Boost Propulsion: Solid rocket. Cruise Thrust: 52.900 kN (11,892 lbf). Cruise Thrust: 5,400 kgf. Maximum speed: 2,260 kph (1,400 mph). Initial Operational Capability: 1953.
Historical Essay © Andreas Parsch
Grumman SSM-N-6 Rigel
In 1946 the U.S. Navy begun the Rigel program to develop a submarine-launched supersonic shore-bombardment missile. The missile was subsequently designated SSM-6, soon changed to SSM-N-6. The Rigel was to be a twin ramjet-powered cruise missile to be launched by a large catapult and multiple solid-propellant rocket boosters. The development program started with launches of several Rigel test vehicles to test the ramjet propulsion system. These test vehicles were of completely different layout than the planned SSM-N-6 tactical missile, and had only a single ramjet and a single in-line rocket booster. The next step the development program were scaled-down FTVs (Flight Test Vehicles) with a configuration similar to the full-scale tactical missile. The first FTV was launched in May 1950.
The operational SSM-N-6 Rigel was designed with two wingtip-mounted Marquardt 71 cm (28 in) ramjets and four rocket boosters. The missile had a range of 930 km (500 nm) and was guided by a modified LORAN system. Two guidance submarines along the flight path would have been used as beacons which were interrogated by the missile to obtain location information. When the predetermined target location was reached, the Rigel would have entered either a preprogrammed or a ballistic flight path towards the point of impact. It was hoped to achieve an accuracy of 550m (600 yd) CEP with this system. The intended warhead for Rigel was a W-5 nuclear fission warhead, but it's possible that the final operational missile would have used a W-27 thermonuclear device.
The full-scale XSSM-N-6 prototypes were to have followed the FTV flight tests, but the Rigel program was cancelled in August 1953, mainly because of repeated failures of the FTVs. By that time, only a mockup of the XSSM-N-6 had been completed. Another reason quoted for the cancellation is that the ramjet-powered Rigel would have required a much longer launch rail than the contemporary turbojet-powered SSM-N-8-RGM-6 Regulus, which would have been a major concern for deployment on submarines.Specifications
Note: Data given by several sources show slight variations. Figures given below may therefore be inaccurate!
Data for XSSM-N-6:
|Length||14.05 m (46 ft 1 in)|
|Wingspan||4.06 m (13 ft 4 in)|
|Diameter||1.14 m (45 in)|
|Weight (incl. boosters)||10800 kg (23800 lb); w-o boosters: 5890 kg (13000 lb)|
|Ceiling||16000 m (52500 ft)|
|Range||930 km (500 nm)|
|Propulsion||Sustainer: 2x Marquardt 28" ramjet; 26.7 kN (6000 lb) each|
Booster: 4x solid-fueled rocket; 35.6 kN (8000 lb) each
|Warhead||W-5 nuclear fission (47 kT)|
 Norman Friedman: "US Naval Weapons", Conway Maritime Press, 1983
 Frederick I. Ordway III, Ronald C. Wakeford: "International Missile and Spacecraft Guide", McGraw-Hill, 1960
 Bill Gunston: "The Illustrated Encyclopedia of Rockets and Missiles", Salamander Books Ltd, 1979
 Kenneth P.Werrell: "The Evolution of the Cruise Missile", Air University Press, 1985
Status: Cancelled 1953.
Gross mass: 11,800 kg (26,000 lb).
Payload: 1,360 kg (2,990 lb).
Height: 14.05 m (46.09 ft).
Diameter: 1.14 m (3.74 ft).
Span: 4.05 m (13.28 ft).
Thrust: 142.10 kN (31,945 lbf).
Apogee: 18 km (11 mi).