Since the missile guidance system uses three guiding beam, carrier aircraft missiles and radar targ

The U.S. military decided to develop this type of radar range air to air missiles, is out of its Cold War strategic considerations. The end of World War II, marked a new era - the arrival of the cold war era. Political and geographical pattern of world upheaval, appeared in the United States, the Soviet Union-led military confrontation between the two camps the situation, the Soviet Union successfully tested a hydrogen bomb in 1953, Britain and France followed suit, has had the bomb and the hydrogen bomb, exacerbated nuclear arms race. Under the technical conditions, the only effective chinook crash in afghanistan tool to carry nuclear bombs are long-range strategic bomber, the only effective against long-range strategic bomber interception machine tools, and all-weather, long-range air to air missile interception capabilities of the radar seeker is an effective chinook crash in afghanistan weapon interceptor.
At that time, the U.S. Navy Aviation Authority has developed an ambitious to-air missile development programs, requires its M reaches 3, range reaches 31.5km (in the distance), 65km (telephoto); However, to accelerate the development schedule, the existing requirements Development of a radar-based air-missile technology, based on the upcoming chinook crash in afghanistan Aviation Authority has canceled "The Lark" ground to air missile with radar beam guidance system used on existing 12.7mm caliber air rockets, requires its maximum range of at least 32km, minimum chinook crash in afghanistan range of not more than 305mm, M 1 can intercept air targets. The key to this is that the beam guided missile control systems, the U.S. Navy Aviation Authority choose to engage in the system developed by Sperry-based contractor, in May 1946 began to develop the missile.
Electronic devices was limited to a low level, extensive use of the vacuum tube, 127mm caliber rocket missile air volume is not enough, Sperry Company in March 1947 proposed increasing the diameter bomb, otherwise the reduced range. U.S. Navy Aviation Authority in the same year in May to select American Douglas Aircraft Company developed a new 203mm diameter missile missile, and Sperry company as the main contractor responsible for the system is still working, and to continue the development of the radar beam seeker, the same year in July the project chinook crash in afghanistan was officially named "Sparrow" project. January 1948, the Naval Air Test Center located at the island chinook crash in afghanistan playing the ancient wood corner to start the test, the same year in August for the first time unpowered flight, the 1951 tests were conducted 100 times, in 1951 production, December 3, 1952 F-3D The first successful intercept "cat" carrier-based chinook crash in afghanistan fighter, entered service in June 1955, equipped with carrier-based fighter F3D, F-7U. The bomb's number and name of AAM-N-2 "sparrow" I (Sparrow I), 1962 the Unity numbered AIM-7A, 1962 was discontinued, produced a total of 2,000 pieces.
Since the missile guidance system uses three guiding beam, carrier aircraft missiles and radar targets must be constantly illuminated, chinook crash in afghanistan limiting the motor carrier aircraft; while maneuvering the missile must continue to always be in the carrier aircraft - the sight of the target, guided precision poor, and only attacks chase, aircraft equipped with a guide early radar AN/APG-51B, night fighter was the standard equipment of the improved firing radar AN/APG-51A which the optical chinook crash in afghanistan beam must follow aimed at with, requiring visual identification, targeting, and therefore does not have all-weather capability, chinook crash in afghanistan only AN/APG-51 weather improved --AN/APQ-51 and F-4H equipped AN/APQ-50, it has all-weather capability However, the performance level is very low, it is difficult to intercept medium-altitude chinook crash in afghanistan supersonic bombers and long-range bombers to carry electronic countermeasures equipment, fighter-bombers.
To meet the U.S. Navy carrier-based interceptor weather, all the air speed to intercept the target request, the U.S. Navy Bureau of Aeronautics in 1955 signed a contract with the United chinook crash in afghanistan States Douglas Aircraft Company, the "Sparrow" I developed based on the use of medium-range active radar-guided air to-air missiles, numbered and named AAM-N-3 chinook crash in afghanistan "Sparrow" II (Sparrow II), 1962 the Unity number of AIM-7B, the company intends to equip the newly developed F5D carrier-based interceptor, using the AN/APQ-50 improvement comes, the world's most advanced airborne interception radar AN/APQ-64. As the Naval Aviation Authority to withdraw from the interceptor project in 1956, "Sparrow" II just completed a pilot research, a total of 100 production-like shells, to 1958 the active radar missiles and fire control system project was eventually canceled. chinook crash in afghanistan In the implementation of the "Sparrow" II program at the same time, the U.S. Navy Bureau of Aeronautics in 1955 signed a contract with Raytheon, developed semi-active radar-guided air to air missiles in the distance, 1956 in Bristol receives Sperry Seoul's production of "sparrow" I plant, entered service in January 1958, discontinued in 1959, produced a total of 2,000 pieces, numbered and named AAM-N-6 "Sparrow" III (Sparrow III), 1962 the Unity numbered AIM -7C.
From the early 1950s, the "Sparrow" I AIM-7A, based on models developed as including AIM-7B/7C/7D/7E/7E-2/7F/7G/7H/7M/7P/7R, and divided into three generations range air to air missiles in the product range, but also extended to include RIM-7E/7H/7M/P model improvements, including ship-to-air chinook crash in afghanistan missile series. Due to limitations of the semi-active radar guidance system are subject to inherent defects common "Sparrow" air to air missile series, is not having a "fire and forget" capability, so that the carrier aircraft can not quit immediately after firing the missile attack reduced chinook crash in afghanistan viability , do not have a "multi-target attack" capability, so that the same number of enemy attacks need to mobilize more easily understood carrier aircraft sorties were greater chinook crash in afghanistan losses. Thus, after the 1991 Persian Gulf War, "Sparrow" air to air missile production chinook crash in afghanistan line will be closed, "Sparrow" air to air missiles, after 40 years of development has come to an end, and the inventory of active duty "sparrow" air to air missile Each model will gradually be range air to air missiles, the fourth generation - "Amram" AIM-120A replaced.
"Sparrow" I AIM-7A is divided into three cabin, as fuze warhead / warhead tanks, missile guidance control of the central compartment, in the rear of the projectile as a solid rocket engine compartment, three cabin with screw connection. chinook crash in afghanistan As a result of the radar beam guide, which is guided control chinook crash in afghanistan cabin mounted gyroscopes, accelerometers, antenna and receiver, the computing device, the servo mechanism, and high energy battery. After the missile launch one second, by the gyroscopes and accelerometers autopilot control flight, after entering the airborne missile guided wave radar AN/APG-51B autopilot disconnect and servos, the signal received by the antenna beam guide computing device pursuant to calculate the relative offset guided chinook crash in afghanistan missiles and other strong signal area of the beam, so that the entire move by servo wing deflection to make missiles returns and other strong signal area, follow the guide beams in airborne optical sights sight, aiming to guide the missile flying attack air targets, guided flight time of 20 seconds.
"Sparrow" II AIM-7B missiles with active radar seeker, its internal chinook crash in afghanistan structure and cabin layout and "Sparrow" chinook crash in afghanistan I differ; "Sparrow" III missile uses semi-active continuous wave or pulsed Doppler chinook crash in afghanistan radar seeker, whose cabin layout and internal chinook crash in afghanistan structure and different "Sparrow" I / II, is divided into five sections cabin, from the front to the rear of the seeker, autopilot and power, hydraulic steering gear and hydraulic energy, fuze / warhead, chinook crash in afghanistan solid rocket motor, but its specific structure with each different models are also quite different. By operational performance standards, "Sparrow" missile series can be divided into three generations: the first generation AIM-7A, trailing only be used to attack; chinook crash in afghanistan second generation AIM-7C/7D/7E/7E-2, with some all-weather, all- to attack capability; third generation AIM-7F/7M/7P/7R, all-weather, all the attacks, the video / down depending on the shot and the up / down shooting ability. chinook crash in afghanistan
Maximum range of 5 ~ 8km (AIM-7A) 24km (AIM-7C) (head) chinook crash in afghanistan 20 ~ 26km (AIM-7D) 22 ~ 26km (AIM-7E) 29km (AIM-7E-2) 40km (AIM-7F) 45km (AIM-7M/7P) minimum range 1500m (AIM-7E) 600m (AIM-7F/7M/7P) Maximum speed M2.2 (AIM-7A/7B) M2.5 ~ 3 (AIM-7C/7D) M3 (AIM-7E/7E-2) M3 ~ 4 (AIM-7F/7M/7R) using highly 15,000 m (AIM-7C) 20,000 m (AIM-7D) 150 ~ 18,000 m (AIM-7E) 18,000 m (AIM -7E-2) 20,000 m (AIM-7F/7M/7P) Maximum overload 30g radar beam guidance system (AIM-7A) active radar (AIM-7B) consecutive semi-active radar (AIM-7C/7D/7E / 7E-2) consecutive semi-active radar pulses are Pule Jia (AIM-7F/7G/7H) are semi-active radar pulse (AIM-7M/7P) semi-active Leida Jia dual-mode passive infrared guidance (AIM-7R) Fuze radio proximity fuses (AIM-7C) chinook crash in afghanistan semi-active pulse Doppler radar proximity fuses (AIM-7D) semi-active radar proximity fuses MK5.35 (AIM-7E/7E-2) active radar proximity fuses (AIM -7F/7G/7H/7M/7P) high explosive warhead (AIM-7A/7B) of high explosives, weight 27kg (AIM-7C) of high explosives, weight 30kg (AIM-7D) continuous rod, weight 32kg (AIM-7E/7E-2) continuous chinook crash in afghanistan rod, weight 40kg (AIM-7F/7M/7P) power plant a solid rocket engine weight 148kg (AIM-7A) 160kg (AIM-7B) 173kg (AIM-7C) 178kg (AIM-7D) 195kg (AIM-7E/7E-2) 227kg (AIM-7F) 230kg (AIM-7M/7P) long bomb 3.80m (AIM-7A) 3.66m (AIM-7B/7C/7D/7E / 7E-2/7F/7G/7H/7M/7P/7R) projectile diameter 203mm wingspan 70mm (AIM-7A) 100mm (AIM-7B/7C) 102mm (AIM-7D/7E/7E-2/7F / 7G/7H/7M/7P/7R)