SSM-N-9 Regulus II

The limited capabilities of the Regulus missile were already evident during its adoption in 1955, so the US Navy developed a specification for a surface-mounted supersonic missile equipped with a similar nuclear warhead with a greater range of fire, accuracy, and resistance to electronic countermeasures.

The development of the Regulus II rocket was in full swing when the program was minimized in favor of the Polaris underwater ballistic rocket, which provided excellent accuracy and could be launched from a submerged position. Subsequently, on the basis of the Regulus II prototype, the Vought KD2U-1 supersonic unmanned aerial vehicle, which was used by the US Navy and the US Air Force to test the IM-99 / CIM-10 Bomarc anti-aircraft missile ^[1], was developed.

Interestingly, the Regulus II SSM-N-9a was reclassified to RGM-15A in June 1963, 5 years after the termination of the program. At the same time, the KD2U-1 unmanned aerial vehicle was renamed the Vought MQM-15A. Some chassis-equipped vehicles were renamed Vought GQM-15A ^[2] .

The main disadvantage of the original Regulus rocket was the radio command control, which required constant radio contact of the rocket with the carrier ship. Another drawback was the short range. For a successful launch of a rocket, the carrier ship had to get close enough to the target and control the flight of the rocket until the moment it hits the target, remaining vulnerable to the means of countering the enemy. Unlike Regulus, Regulus II was equipped with the inertial autopilot of AC Sparkplug, which does not require control from the ship after launch. Thanks to better aerodynamics, more fuel, and better engine fuel efficiency, the Regulus II had a significantly longer range ^[1] .

The prototype of the rocket, designated as XRSSM-N-9 Regulus II was equipped with a retractable landing gear, providing the possibility of multiple launches. The rocket had engines and accelerators Aerojet General , which did not allow her to develop supersonic speed. The first launch of the XRSSM-N-9 was carried out on May 29, 1956 at Edwards Air Base . Since 1958, testing of the XRSSM-N-9a modification with the General Electric J79-GE-3 turbojet engine and the Rocketdyne solid-fuel booster , which fully provided the specifications, was carried out. Test and training versions of the retractable missile chassis were produced under the name YTSSM-N-9a and TSSM-N-9a, respectively ^[2] .

After ground testing, the tests continued on board the landing ship LST-857 King County, where the launcher designed for submarines was mounted.

The SSM-N-9 Regulus II was intended for launching from the deck of a missile submarine (SSG) in surface position. Planned to install on submarines and SSGN-587 "Halibat" , and then on 4 surface missile cruisers and 23 other submarines. Ammunition was up to 5 missiles, which were located in the interior of the hangar. Vessels and boats were equipped with an inertial navigation system (SINS), which made it possible to adjust the rocket navigation system before launch ^[1] .

48 Regulus II test runs were performed, including 30 successful, 14 partially successful and 4 unsuccessful. In January 1958, a contract was signed for the industrial production of missiles. In September 1958, the first and only launch of a missile from a submarine (SSG-574 Greyback) was made ^[1] .

Due to the high cost (about $ 1 million per unit), budget constraints and the emergence of Polaris missiles, on November 19, 1958, the Regulus missile production program was curtailed. The final closure of the program took place on December 18, 1958 by Secretary of the Navy Thomas Gates . By the time production ceased, Vought launched 20 rockets, another 27 were on the conveyor ^[1] .

The design of the rocket is similar to that of a conventional aircraft; lightweight materials and alloys are used to save weight. The fuselage is tubular, conical in the nose where the guidance equipment, warhead and system equipment is located. Under the central part of the body was a characteristic wedge-shaped air intake.

Swept wings were installed in the middle part of the fuselage, arrow-shaped stabilizer was located above the tail section, sometimes it was supplemented with a small additional stabilizer under the tail section.

The rocket was controlled by ailerons located on the rear edge of the outer wing. The tail wings of the rocket were missing, the steering wheel was located on the rear edge of the stabilizer. The flaps were placed on the rear edge of the inner part of the wing and used at launch. For additional stabilization and pitch control, small trapezoidal wings were designed in the forward fuselage.

To launch the rocket, the carrier ship was raised to the surface (if it was a submarine) and put the rocket on the launcher. After that, the rocket was connected to the ship’s navigation system to enter the coordinates of the target and synchronize the inertial autopilot. After bringing the missile into readiness and obtaining permission to launch, the main engine, afterburner and powder accelerator were turned on, the rocket left the launcher and went to the target in an autonomous mode.

After folding the program ready and under construction copies were converted into supersonic unmanned targets KD2U-1, hereinafter referred to as MQM-15A and GQM-15A. Targets were used to train the calculations of anti-aircraft missile systems CIM-10 Bomarc , located on about. Santa Rosa . Launches were carried out from the Eglin-Gulf test site in the area of Fort Walton Beach (pcs. Florida ). Since September 3, 1959, 46 launches of 13 rockets were conducted. Then the remaining missiles were transported on September 30, 1961 to the Roosevelt Roads base to Puerto Rico to test Tartar, Terrier, and Talos missiles. Upon completion of testing in 1963, the missiles were transferred to Point Mugu ( California ), where they were used until December 1965 ^[1] .

Museum of Aviation Pioneers (Frontiers of Flight Museum), Dallas Love Field , Texas

Regulus ii

Point Mugu Missile Park, US Navy Point Mugu California

Museum exposition includes Regulus and Regulus II rockets

Veterans Memorial Museum, Huntsville , Alabama

Regulus ii

Modifications

• SSM-N-9 Regulus II - the basic model.
• Regulus II SSM-N-9a is the designation of the industrial model.
• The XRSSM-N-9 Regulus II is an experimental model with retractable landing gear, Wright J65 engines and Aerojet General rocket boosters.
• The XRSSM-N-9a is an experimental model with a retractable landing gear, General Electric J79 engines and a Rocketdyne rocket accelerator .
• YTSSM-N-9a is an experimental training model with retractable landing gear.
• The TSSM-N-9a is an industrial version of an experimental training model with a retractable landing gear.
• The RQM-15A is a model upgraded in April 1963.
• The MQM-15A is the KD2U-1 unmanned aerial vehicle used for research and as a target for the IM-99 Bomarc anti-aircraft missile system.
• GQM-15A - upgraded unmanned vehicle with chassis.

• US Navy
• USAF

• en: List of missiles
• en: SSBN Deterrent Patrol insignia

• Werrell, Kenneth P. The Evolution of the Cruise Missile. - Maxwell Air Force Base, Alabama: Air University Press, 1985. - 289 p.
• Gibson, James N. Nuclear Weapons of the United States: An Illustrated History. - Atglen, Pennsylvania: Schiffer Publishing Ltd., 1996. - 240 p. - (Schiffer Military History). - ISBN 0-7643-0063-6 .

• Carolinas Aviation Museum (inaccessible link from 02-09-2013 [2153 days] - history , copy )
• Vought SSM-N-9 / RGM-15 Regulus II
• Regulus II RGM-15A SSM-N-9
• USS HALIBUT (SSG (N) 587)
• US NAVY RGM-6 REGULUS / RGM-15 REGULUS II
• REGULUS II CRUISE MISSILE
• Regulus 2
• Chance Vought Regulus II (1950s)
• YD Floating Crane (Non Self Propelled) . NavSource Online: Service Ship Photo Archive
• Regulus ii cruise missile