SAM "BOMARC" CIM-10A / B ("BOMARK")
The "Bomark" SAM was developed to provide air defense to large areas of the United States and Canada. This is a stationary anti-aircraft complex.
The peculiarity of the construction of the complex units is that the detection and target designation system, as well as control means rockets service several launchers located at a considerable distance from each other.
The contract for the development of the US Air Force complex was concluded with the Boeing company and the subcontractor of the Michigan Aeronautical Research Center at 1951.
The development of the air defense missile system was accompanied by disputes between American specialists about the optimal structure. Defense territories of the United States and Canada. Air Force specialists believed that this defense should be built on the basis of systems with an interception range of about 400 km or more, thereby providing coverage for significant areas and zones. Army specialists defended the concept of "point", object-based air defense, which envisages the use of medium-range air defense systems located around individual defended objects.
Zaur "Bomark" on the starting position, 1956,
The military-economic studies conducted in the USA showed the advantage of the point of view of the Air Force specialists: the cost of such complexes is about two times lower; they require maintenance staff almost seven times less; The area occupied by combat means is almost 2,5 times smaller. However, for reasons of ensuring “defense in depth”, the US military command approved both concepts.
A distinctive feature of the Bomark air defense missile system is that it does not incorporate a detection and target indication system, as well as a significant part of the SAM control systems. The functions of these means and systems are performed by the unified semi-automatic air defense control system of the territories of the USA and Canada “Sage”, which simultaneously manages the operations of fighter-interceptors and other air defense systems.
With such a construction, the Bomark air defense system practically only needed to develop a rocket interacting with the Sage system and a launcher for it.
Flight tests Zour "Bomark", August 1958,
Initially, the complex received the designation XF-99, then IM-99 and only then CIM-10A.
Tests of the propulsion system for the Bomarck missile launcher began in the 1951 year. Flight testing began at the end of June 1952, but due to lack of equipment, testing was postponed until 10 September 1952. The second tests were 23 January 1953 g. On the site "Cape Canaveral", and the third - 10 June 1953. An 1954 launch was performed on 3. At the end of the test, in 1958, 25 rockets were launched and the program was transferred to tests at the Santa Rosa Island test site. During the test 1952-1958. At the "Cape Canaveral" training ground, approx. 70 rockets. By 1 December 1957, the "Air Proving Ground Command" and "Air Force Armament Center" were combined into a single air defense test center "Air Proving Ground Center", where Bemark was later tested.
There are two modifications of the Bomark air defense missile system - A and B, which were adopted by the air defense of the territories of the USA and Canada in the 1960 and 1961 years, respectively. They differ in maximum combat range and flight altitude (which is achieved mainly due to the power of the cruising engine), the type of launching accelerator and the type of radiation of the active radar homing head. Their maximum combat ranges are 420 and 700 km, respectively. The transition to the GOS from pulsed radiation (option A) to continuous (modification B) increased the ability of the missile defense system to intercept low-flying targets.
Zaur "Bomark" in the Museum of the US Air Force
The commands for guiding the Bomark missile system are generated by a digital computer of the Sage system’s air defense center's guidance center and transmitted via underground cables to the radio command transmission station, from where they come aboard the missile. In this computer data is entered on the targets received from the numerous radar detection and identification system "Sage".
The launcher for the missiles of both versions is the same. It is stationary, designed for one rocket and provides its vertical launch. The 30-60 launchers built alongside make up the SAM system, a launching pad. Each such base is connected by underground cables to the corresponding center of the Sage system, which is located at a distance from 80 to 480 km from it.
There are several types of launch hangars for the Bomark air-defense system: with a sliding roof, with sliding walls, etc. In the first version, the block reinforced concrete shelter (length 18,3, width 12,8, height 3,9 m) for the launcher consists of two parts: the starting compartment, which is mounted the launcher itself, and the compartment with a number of rooms where the control instruments and equipment for launch control of the missiles are located. To bring the launcher into a firing position by hydraulic actuators operating from a compressor station, the roof flaps are moved apart (two shields with a thickness of 0,56 and weight of 15 and each). The rocket boom from horizontal to vertical position. It takes up to 2 minutes for these operations, as well as for switching on the onboard equipment of the missile defense system.
The SAM base consists of an assembly and repair shop, launchers proper and a compressor station.
In the assembly and repair shop, rockets are assembled, which arrive unassembled at the base in separate transport containers. In the same workshop, the necessary repairs Zur.
The layout scheme of the Boomark A (a) and Bomark B (B):
1 - homing head; 2 - electronic equipment; 3 - combat compartment; 4 - combat compartment, electronic equipment, electric batteries; 5 - RAMJET
The Bomark air-launched anti-aircraft missile of modifications A and B is supersonic (maximum flight speeds 850 and 1300 m / s, respectively) and has an airplane circuit (similar to the Soviet Tu-131 projectile). It flies at maximum range and altitude with two liquid-propellant ramjet marching engines operating (active flight stage). The LRE was used as the launching accelerator in rocket A, and the solid propellant rocket motor was used in rocket B.
In appearance, modifications of rockets A and B differ little from each other. Their starting weight is 6860 and 7272 kg; length 14,3 and 13,7 m, respectively. They have the same diameters of the hulls - 0,89 m, wingspan - 5,54 m and stabilizers 3,2 m.
The head radio transparent body fairing ZUR, made of fiberglass, covers the homing head. The cylindrical part of the hull is mainly occupied by a steel supporting tank for liquid fuel ramjet fuel.
Swivel wings have a sweep leading edge 50 hail. They do not rotate entirely, but have a triangular aileron at the ends - each console around 1 m, which provide flight control along the course, pitch and roll.
Start Zaur "Bomark"
As an active radar homing head for missiles used upgraded aircraft radar interception and aiming. The rocket A GOS pulse, operating in a three-centimeter range of radio waves. The rocket B has a head with continuous radiation, using the principle of selection of a moving target for Doppler velocity. This allows you to direct missiles at low-flying targets, targets - directing jammers. The range of action of the GOS is 20 km.
The warhead weighing about 150 kg can be normal or nuclear. The TNT equivalent of a nuclear warhead - 0,1 - 0,5 Mt, which is said to ensure the destruction of the aircraft in the event of a miss to 800 m.
To power on-board equipment Zour used silver-zinc batteries.
The launch accelerator for the rocket A is a rocket engine operating on kerosene with the addition of asymmetric dimethyl hydrazine and nitric acid. This engine runs 45 seconds, accelerating the rocket to the speed at which the ramjet is activated at an altitude of about 10 km.
In the rocket In the launch accelerator is a solid propellant rocket motor, the body of which is separated after the fuel burns out. The use of solid-propellant rocket motors instead of rocket engines has reduced the time for acceleration of missiles, simplified operation and increased the reliability of the rocket.
In both versions of the anti-aircraft missiles, two liquid fuel jet engines were used as cruise engines, reinforced on a pylon under the rocket body. The diameter of each of these engines is 0,75, and the length of 4,4 is m. The fuel is petrol with an octane rating of 80.
Ramjet missiles are most effective at cruising altitude. For missile A, it is 18,3 km, and for missile B, 20 km.
The scheme of action of the Bomark air defense missile system against the commands of the Sage system:
1 - launchers (hangars); 2 - the starting part of the trajectory; 3 - marching trajectory; 4 is the end section of the trajectory; 5 - interceptors battalion command center; 6 - data lines; 7 - reports on the state of military equipment; 8 - pre-start data; 9 is the operational center of the Sage system; 10 - command transmission station aboard missiles; 11 - radar long-range detection of the air defense sector; 12 - radar target information and missiles; 13 - guidance commands.
The controlled trajectory of the Bomarck missile to the target is divided into three sections.
The first, vertical - section of the climb. In rocket A, before reaching the supersonic speed, program gas-dynamic control is carried out due to the turns on the cardan of the starting LRE, and upon reaching this speed - aerodynamic control of ailerons. In missile B, due to more intense acceleration by starting solid propellant solid propellant rotors, effective aerodynamic control becomes possible much earlier. Vertically, the missile system flies to the height of a cruising flight, then turns around. By this time, the tracking radar detects it and switches to auto tracking using an on-board radio responder.
The second, horizontal - section of the cruise flight at cruising altitude in the area of the target. Television commands in this area come from the Sage radio command station. Depending on the maneuvers of the target, the type of the ZUR flight trajectory in this area may vary.
The third area is the area of direct attack of the target, when, using radio commands from the ground, the active radar homing missile defense system searches for a target. After the target is “captured” by the target head, communication with ground-based television telescopes is stopped, and the rocket flies, aiming autonomously.
Modernization
In 1961, an improved modification of the Bomark "Super Bomark" IM-99В is adopted.
Conclusion
Zaur "Bomark" in the Museum of weapons of the US Air Force
The missiles of this complex were protected 6 strategic facilities in the United States and two - in Canada.
Both types of missiles are decommissioned in the 1972 year.
Information