Hỏa tiễn tầm nhiệt SA-7

Nhận dạng tử thần : Hỏa tiễn tầm nhiệt SA-7

Khai hoả 589 lần, trúng đích 204 lần các mục tiêu trên không gồm các loại phi cơ của Không Quân Mỹ và VNCH từ năm 1972-1975, tỉ lệ hiệu quả khoảng 1/3, so sánh với các con số như trong cuộc chiến Trung Đông từ 1969 đến 1970 quân đội Ai Cập khai hỏa 99 lần và trúng 36 phi cơ chiến đấu của Israel (tỉ lệ khoảng 1/3) hay vào năm 1974 quân đội Syrie đã hạ gục 11 chiếc của Israel đã phản ảnh một điều: SA-7 quả thật có khả năng hạ bất cứ phi cơ nào trong tầm, nhất là trong các cuộc chiến du kích vì tính nhỏ gọn, cơ động.
Chúng ta chỉ nghe nói về loại hỏa tiễn tầm nhiệt SA-7 khi về Phi Đoàn cũng như được chỉ dẫn một vài phương cách đối phó, tuy nhiên vẫn chưa có hân hạnh "nếm" qua trên chiến trường, một sự mai mắn lớn. SA-7, nỗi kinh hoàng trên không của những Pilot VNCH trong cuộc chiến bảo vệ miền Nam VN trước đây, đã gây nhiều thiệt hại cho không quân VNCH, nhất là ngành trực thăng với cao độ và tốc độ đều nằm trong tầm phóng lý tưởng của loại hỏa tiễn tầm nhiệt cá nhân nầy. Với tốc độ trung bình của trực thăng khoảng 120 knots (khoảng 220 km/h) so với tốc độ mach 1.25 của SA-7, dù phi hành đoàn có cảnh giác cao độ, khi cặp mắt nhìn thấy làn chớp xanh lóe lên thì hỏa tiễn đã đến nơi. Một loạt các biện pháp để đối phó như xử dụng flare làm mục tiêu giả, thay đổi hướng bay, cao độ...nhưng đáng kể nhất là việc tân trang đời UH-1H với ống thoát hơi phản lực hướng lên main rotor để lấy sức cánh quạt thổi hơi thoát làm giảm đi sức nóng tập trung có thể làm mồi cho SA-7.

Đến hôm nay SA-7 vẫn còn được xử dụng tại một số chiến trường, dĩ nhiên với nhiều cải tiến đáng sợ hơn. Xin góp nhặt một số chi tiết cống hiến cùng các bạn.


Mang ký hiệu "SA-7 Grail" của khối NATO để chỉ loại hỏa tiễn địa không "Strela-2" cùa Nga, ký hiệu 9K32, chúng ta quen gọi là hỏa tiễn tầm nhiệt SA-7, là loại hỏa tiễn cá nhân rất cơ động, có thể khai hỏa trên vai người lính bộ binh, được điều khiển bằng tia hồng ngoại, tương tự như loại hỏa tiễn FIM-43 Redeye của Hoa Kỳ. Được chế tạo tại Nga vào năm 1968, tuy nhiên bộ phận dò tìm hồng ngoại không được chính xác lắm và thường bị lạc hướng do mặt trời hay các nguồn nóng khác từ mặt đất. Vào năm 1972 Strela-2 được thay thế bởi Strela-2M tức loại SA-7B theo codename của NATO (GRAU-index 9K32M) với sự nhiều cải tiến về vận hành, tốc độ nhanh và tầm hoạt động hiệu quả hơn, cũng như thay thế bộ phận dò tìm IR mới.
"Dàn" SA-7 bao gồm một hỏa tiễn 9M32 hoặc 9M32M, một ống phóng với bộ phận nhắm, bộ phận kích hỏa điện tử (9P54 hay 9P54M) với tay cầm và một battery nhiệt điện. Ngoài ra còn có một bộ phận nhận tín hiệu IFF ( Identification Friend or Foe) được gắn vào helmet của người bắn để có thể nhận dạng mục tiêu bạn và thù và antene nhận tín hiệu bằng âm thanh được gắn vào ống nghe của xạ thủ để dò kiếm và nhắm mục tiêu.
Hỏa tiễn chỉ cần 6 giây để sẵn sàng khai hỏa: Sau khi mở contact điện, xạ thủ theo dõi mục tiêu với ống nhắm và bóp cò. Ngay lập tức bộ phận dò tìm của hỏa tiễn được khởi động và nhắm bắt mục tiêu. Một khi tín hiệu nhận về đủ mạnh và tốc độ góc nằm trong tầm, một đèn đỏ báo hiệu bật sáng với một tín hiệu kéo dài. Xạ thủ sẽ phải giữ đúng mục tiêu trong vòng 0,8 giây cho đến khi hỏa tiễn khai hỏa. Nếu mục tiêu nhắm bị sai lệch hay mất đi xa thủ sẽ nhận tín hiệu khác đi và sẽ phải nhắm bắt mục tiêu lại.
SA-7 có 4 tầng: tầng đầu là đầu dò tìm, tầng thứ 2 có cánh lái để điều khiển hướng bay (bằng cách thay đổi góc của cánh lái) mang chất nổ, tầng thứ 3 là động cơ chính chứa nhiên liệu đặc, tầng cuối cùng là động cơ khởi động. Phần cuối của hỏa tiễn có các cánh ổn định.
Đầu tiên, tầng cuối cùng (booster-Motor) trong ống phóng khai hỏa và đẩy hỏa tiễn ra với tốc độ 30 m/s và xoay 20 vòng mỗi giây (20 U/s). Sau khi rời ống phóng, các cánh bình ổn trước và sau xòe ra khoảng 30 cm, đồng thời bộ phận tự hủy cũng khởi động và hỏa tiễn sẽ phát nổ sau 17 giây nếu không tìm được mục tiêu để tránh thiệt hại dưới đất. Ngay sau khoảng 0,3 giây với khoảng cách 5 m, động cơ hỏa tiễn khai hỏa đẩy vận tốc tăng lên 430 m/s (Mach 1,25 ) và sau khỏang 120 m thì chốt an toàn cuối cùng tự mở, hỏa tiễn sẵn sàng tiêu diệt mục tiêu.
Bộ phận dò tìm ở tầng đầu hỏa tiễn xử dụng cơ phận bán dẫn có phản ứng với tia hồng ngoại có làn sóng cực ngắn 0,2 đến 1,5 µm. Khi bắt gặp mục tiêu trong tầm dò tìm, hỏa tiễn tự động điều chỉnh hướng chính xác và lao vào mục tiêu, chất nổ chứa trong khoang thứ nhì sẽ nổ tung khi va chạm. Mặc dù nó không thể phá hủy hoàn toàn phi cơ nhưng gây thiệt hại nặng và nếu trúng vào chỗ "nhược" như bình xăng, cánh lái hay động cơ, cánh quạt...thì kể như "đi không ai tìm xác rơi".

Đặc tính kỷ thuật: 9K32M Strela-2M

Tốc độ: 430 m/s - Mach 1.25
Tầm hoạt động: 800 - 4200 m
Cao độ: 30 - 2300 m
Động cơ: nhiên liệu đặc
Trọng lượng: 9.15 kg
Ống phóng : 4.17kg
Chất nổ: 1,8 kg HTA
Chiều dài: 1,438 m
Đường kính: 72 mm
Cánh : 30 cm
Hệ thồng hướng dẫn : Infra-red passive homing
Bộ phận tự hủy : 14 - 17 second delay self-destruct


Xử dụng:

Vào thời chiến tranh lạnh, quân đội Sô Viết được trang bị hỏa tiễn SA-7 rộng rãi cùng với các nước trong khối Varsovie với nhiều thay đổi và cải tiến. Nhiều quốc gia vẫn còn xử dụng cho đến hôm nay.
Như trên đã đề cập, SA-7 cũng được xử dụng nhiều trong các cuộc chiến như Trung Đông, Việt Nam...(xem bảng số liệu từ http://en.wikipedia.org/wiki/Strela_2) nhưng nguy hiểm nhất là một số vẫn đang còn trong tay bọn khủng bố.
Tháng 11. 2002 một chiếc Boeing 757 của hãng hàng không Do Thái El Al chở đầy hành khách mai mắn thoát khỏi tai họa do hỏa tiễn SA-7 chỉ trong gan tấc. Bọn khủng bố có lẽ trong vội vàng đã khai hỏa 2 hỏa tiễn SA-7 mà không kịp chờ đến khi phi cơ bay ngang tầm để nhắm vào tia phụt hậu của động cơ và nhờ thế, đầu dò tìm của hỏa tiễn không thể nhắm bắt mục tiêu và chệch đường nổ tung, âu cũng là phước lớn.
Cũng trong năm 2002 theo nguồn tin của Irak, một pilot MiG-23ML của không quân Irak trở cờ tấn công vào dinh Tổng Thống Irak lúc đó là Saddam Hussein, quân phòng ngự đã bắn hạ chiếc MiG-32 nầy với một SA-7 !
Ngày 2 tháng 11. 2003 một chiếc Chinook CH-47 của quân đội Mỹ bị trúng phải 2 trái SA-7 tại Fallujah, Irak làm 15 binh sĩ thiệt mạng.

Các quốc gia đang xử dụng:

Afghanistan, Albania, Algeria, Angola, Armenia, Botswana, Benin, Bulgaria, Burkina Faso, Cambodia, People's Republic of China, Croatia, Cuba, Cyprus, Czech Republic, Czechoslovakia, Egypt, Ethiopia, Finland (Withdrawn from service), East Germany, Germany (former East German Army assets), Ghana, Guinea-Bissau, Hungary, Indonesia, India (being withdrawn from service), Iraq, Iran (passed to Hezbollah), Kuwait, Laos. Lebanon. Libya, Macedonia, Mauritania, Morocco, Mozambique, Nicaragua, North Korea, Pakistan, Peru, Poland, Romania, Sierra, Serbia, Slovakia, Slovenia (in reserve), Somaliland, South Yemen, Soviet Union, Sudan, Syria, Tanzania, Ukraine, Vietnam, Yugoslavia, Zambia, Zimbabwe, Tamil Eelam. Many other countries, along with numerous Terrorist and Paramilitary groups.

DOUGLAS B-26B IN VIETNAM

After the end of the Korean War, the B-26B was gradually replaced by newer and more advanced aircraft. By the late 1950s, the B-26 was only used for liaison missions, such as staff transport . However, with the continuing internal problems in South Vietnam combined with the increasing activities of the North Vietnam sponsored Viet Cong, President Kennedy decided to provide military assistance to South Vietnam. The initial stated purpose of U.S. involvement was to provide advisors and training in support of counter insurgency operations. The USAF's 4410th Combat Crew Training Squadron (CCTS) was assigned to this mission. B-26s were pulled from storage and readied for reconnaissance and combat duties before being sent to Vietnam. The first aircraft began arriving in late 1961 as part of Operation Farm Gate. These aircraft initially had South Vietnamese markings and were designated RB-26s, but were fully combat capable. The South Vietnamese training mission was only a minor part of Farm Gate and nearly all missions were flown by USAF crews occasionally accompanied by a South Vietnamese crew member. Counter insurgency operations continued while the 4410th CCTS mission gradually expanded to include some close air support and escort duties. For example, the B-26 was used to escort C-123s flying Operation Ranch Hand defoliation missions. When two B-26s crashed because of structural failures, the aircraft were withdrawn from combat in 1964. For the B-26B, this was the end of its combat service. An improved and rebuilt version of the B-26 would return to Vietnam for combat duty in the late 1960s. This aircraft was initially designated B-26K and later re-designated A-26A.
Type
Number built/converted
Remarks
B-26B*
1,355**
Light Attack Bomber*The A-26B was re-designated B-26B in 1948 after the USAF dropped the attack designation **1355 A-26Bs built and accepted by the Army Air Force; however, at least 25 more were completed but never delivered to the AAF. These aircraft (on canceled contract AC-21393) were direct delivered from the factory to the Kingman reclamation center (RFC) beginning in October 1945. Known serial numbers are 44-34754 to 44-34775; 44-34777 to 44-34779. (Source: Individual Aircraft Record Cards stored at the AFHRA)TECHNICAL NOTES (Typical for late block B-26B): Armament: Two .50-cal. machine guns in a dorsal barbette, two .50-cal. machine guns in a ventral barbette (sometimes omitted in favor of an extra fuel cell), eight forward-firing .50-cal. machine guns in the nose and six .50-cal. machine guns in the wings, plus provisions for 6,000 lbs. of bombs (4,000 lbs. internal and 2,000 lbs. external on wing racks), 14 5-inch rockets could be carried in place of the wing-mounted bombsEngines: Two Pratt & Whitney R-2800-27 (or -71 or -79) radials of 2,000 hp eachMaximum speed: 322 mph Cruising speed: 278 mph Range: 2,900 miles maximum ferry range Service ceiling: 24,500 ft. Span: 70 ft. 0 in. Length: 50 ft. 8 in. Height: 18 ft. 6 in. Weight: Approx. 41,800 lbs. gross takeoff weight Crew: Three (pilot, navigator, gunner) Serial numbers: 41-39100 to 41-39151; 41-39153 to 41-39192; 41-39194; 41-39196 to 41-39198; 41-39201 to 41-39599; 43-22252 to 43-22303; 43-22305 to 43-22307; 43-22313 to 43-22345; 43-22350 to 43-22466; 44-34098 to 44-34753 Click here to return to the Attack Aircraft index.
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F-5 A-E NORTHROP

The F-5 is a supersonic fighter combining low cost, ease of maintenance and great versatility. More than 2,000 F-5 aircraft have been procured by the USAF for use by allied nations. The F-5, which resembles the USAF Northrop T-38 trainer, is suitable for various types of ground-support and aerial intercept missions, including those which would have to be conducted from sod fields in combat areas.


The F-5 first flew on July 30, 1959, and deliveries to the Tactical Air Command for instructing foreign pilots began in April 1964. Pilots from Iran and South Korea were the first to be trained in the F-5, followed by pilots from Norway, Greece, Taiwan, Spain and other Free World nations that have adopted the F-5. A two-place combat trainer version, the F-5B, first flew in February 1964. In 1966-1967, a USAF squadron of F-5s flew combat missions in Southeast Asia for operational evaluation purposes.

The National Museum of the United States Air Force has a YF-5A on display in its Modern Flight Gallery.


Type Number built/
converted Remarks
YF-5A 3 Prototype
F-5A 621 Lightweight fighter
RF-5A 89 Photo-recon A model
F-5B 134 Two-seat trainer
F-5E 1,144 Improved A model
RF-5E * Photo-recon E model
F-5F 233 Two-seat trainer
F-5G * Norwegian A model
RF-5G * Photo-recon G model; from RF-5A


Notes:
* = not used by USAF
- CF-5A and B were built in Canada for the Canadian Air Force.
- NF-5A and B were Royal Netherlands Air Force aircraft.
- SF-5A and B (C-9/CE-9) were CASA built aircraft for the Spanish Air Force.
- The RF-5E photo-reconnaissance variant was known as the "Tiger Eye."
- The F-5G was the Royal Norwegian Air Force variant of the F-5A known as the "Tiger Shark."
- The RF-5G was the Royal Norwegian Air Force variant of the RF-5A.


TECHNICAL NOTES (F-5A):
Armament: Two 20mm cannons, rockets, missiles and 5,500 lbs. of bombs externally
Engines: Two General Electric J85s of 4,080 lbs. thrust each with afterburner
Maximum speed: 925 mph
Cruising speed: 575 mph
Range: 1,100 miles
Service ceiling: 50,700 ft.
Span: 25 ft. 10 in.
Length: 47 ft. 2 in.
Height: 13 ft. 6 in.
Weight: 20,576 lbs. loaded


NORTHROP F-5 TIGER II


The F-5E Tiger II was a greatly improved version of the earlier F-5A Freedom Fighter. Redesigned as a highly maneuverable, lightweight and inexpensive air superiority fighter, the E model featured an air-to-air fire control radar system and a lead computing gunsight. More powerful J85 engines required the fuselage to be both widened and lengthened. The forward wing root was redesigned to give the "Tiger II" wing its characteristic triple delta shape. The first flight of the F-5E was on Aug. 11, 1972. The first USAF unit to receive the aircraft was the 425th TFS at Williams Air Force Base, Ariz., responsible for training foreign pilots in the F-5 aircraft. The most well-known use of the "Tiger II" was as an aggressor aircraft at the USAF Fighter Weapons School, Nellis Air Force Base, Nev. The aggressor pilots of the 64th Fighter Weapons Squadron were trained in Soviet tactics and used the Es to similate MiG-21s for training USAF pilots in aerial combat skills. Eventually, aggressor squadrons were formed at RAF Alconbury, U.K., and Clark AB, PI, for training USAF pilots stationed overseas along with pilots of friendly foreign nations.


Type Number built/
converted Remarks
YF-5A 3 Prototype
F-5A 621 Lightweight fighter
RF-5A 89 Photo-recon A model
F-5B 134 Two-seat trainer
F-5E 1,144 Improved A model
RF-5E * Photo-recon E model
F-5F 233 Two-seat trainer
F-5G * Norwegian A model
RF-5G * Photo-recon G model; from RF-5A


Notes:
* = not used by USAF
- CF-5A and B were built in Canada for the Canadian Air Force.
- NF-5A and B were Royal Netherlands Air Force aircraft.
- SF-5A and B (C-9/CE-9) were CASA built aircraft for the Spanish Air Force.
- The RF-5E photo-reconnaissance variant was known as the "Tiger Eye."
- The F-5G was the Royal Norwegian Air Force variant of the F-5A known as the "Tiger Shark."
- The RF-5G was the Royal Norwegian Air Force variant of the RF-5A.

TECHNICAL NOTES (F-5E):
Armament: Two M-39 20mm cannons, rockets, missiles and 5,500 lbs. of bombs externally
Engines: Two General Electric J85-GE-21s of 5,000 lbs. thrust each with afterburner
Maximum speed: 1.63 mach at 36,000 ft. (1,050 mph)
Cruising speed: 650 mph
Range: 2,300 miles (maximum with external fuel tanks)
Service ceiling: 50,700 ft.
Span: 26 ft. 8 in.
Length: 48 ft. 2 in.
Height: 13 ft. 4 in.
Weight: 24,675 lbs. maximum takeoff weight

A-37A, A-37B CESSNA

CESSNA A-37 DRAGONFLYhttp://www.nationalmuseum.af.mil/factsheets/factsheet.asp?id=326

From 1964-1966, the U.S. Air Force evaluated two modified T-37 trainers, designated YAT-37Ds, as prototypes for a counter-insurgency (COIN) attack/reconnaissance aircraft to use in Southeast Asia. Following this evaluation, the USAF contracted Cessna to modify 39 T-37Bs into A-37As in 1967. Later that year, the USAF sent 25 A-37As, nicknamed "Super Tweets," to Southeast Asia for combat evaluation under the name Combat Dragon. These aircraft primarily flew close air support, night interdiction and forward air control missions in South Vietnam and southern Laos.

Based on the successful results of Combat Dragon, the USAF order newly built A-37Bs, which had cockpit armor, more powerful engines, redundant flight controls, provision for aerial refueling and a strengthened airframe. Of the 577 A-37Bs built, the USAF provided 254 to the South Vietnamese Air Force (VNAF) to replace their aging A-1 Skyraiders. Although the A-37B served with the USAF for only a short period, a number of A-37Bs remained in use with the Air Force Reserve and Air National Guard as observation/flight attack aircraft until the last one was retired in 1992.

The aircraft on display was one of the two prototype YAT-37Ds evaluated by the USAF. It was retired to the museum in December 1964. However, it was recalled to active service in August 1966 for final design testing of the urgently needed A-37 attack aircraft. This aircraft retired to the museum for a second time in July 1970 as the YA-37A.

TECHNICAL NOTES:
Armament: One 7.62mm minigun and 3,000 lbs. maximum of bombs, rockets and/or missiles
Engines: Two 2,400-lb. thrust General Electric J85s
Maximum speed: 485 mph
Cruising speed: 425 mph
Range: 270 miles with 3,000 lb. load
Ceiling: 36,000 ft.
Span: 35 ft. 10 in.
Length: 29 ft. 4 in.
Height: 8 ft. 2 in.
Weight: 11,700 lbs. maximum
Serial number: 62-5951  

Cessna A-37A (S/N 67-14513) of the 605th Special Operations Squadron, Bien Hoa Air Base, South Vietnam. Aircraft burned after an emergency landing in October 1968. (U.S. Air Force photo)

 Cessna A-37A (S/N 67-14514) at Bien Hoa Air Base on Aug. 16, 1967. (U.S. Air Force photo)

 Cessna A-37A (S/N 67-14504) at Bien Hoa Air Base, South Vietnam. (U.S. Air Force photo)

 Cessna A-37A in flight. (U.S. Air Force photo)

Cessna A-37A of the 8th Tactical Fighter Wing over Vietnam in September 1972. 

(U.S. Air Force photo)

Cessna A-37A (S/N 67-14516) firing rockets while in flight in Vietnam. (U.S. Air Force photo)

Cessna A-37A at Bien Hoa Air Base, South Vietnam, in August 1967. (U.S. Air Force photo)

 

On Aug. 23, 1966, the USAF directed the establishment of a program to evaluate the A-37 in a combat environment. The project was named "Combat Dragon" and was designed to test the effectiveness of the A-37 in Close Air Support, counterinsurgency and escort missions in Vietnam. Besides testing the aircraft operationally, the project was also used to evaluate the maintenance, supply and manpower requirements. The Tactical Fighter Weapons Center directed the program and established a 350-man squadron with 25 A-37As at England Air Force Base, La. in early 1967. The unit was designated as the 604th Air Commando Squadron. Initial instructor pilot training began on March 29, 1967. Initial operations and combat orientation started on May 1. Phase I of Combat Dragon was done between June 19 and July 16, 1967 at England Air Force Base. Phase I measured data collection and analysis procedures to be used during the actual combat evaluation, train the A-37A pilots, establish a bombing and gunnery baseline and identify and fix problems with the aircraft.

The 604th ACS was moved to Bien Hoa Air Base, South Vietnam, between July 17 and Aug. 14, 1967. Phase II of Combat Dragon began on Aug. 15 and ended on Sept. 6. This phase of the project was used to familiarize the pilots was the operational areas of Vietnam and Laos. The data collection and evaluation system was also refined using forms and methods already in use in Southeast Asia. Phase III of Combat Dragon began on Sept. 7 and the first actual ground strike missions were flown. Phase III operations continued until Oct. 27. Phase IV of Combat Dragon was done between Oct. 28 and 30 and tested accelerated (maximum sortie generation) mission scheduling. Phase V began on Nov. 1 and tested the ability of the aircraft to operate from a forward operating location. Seven aircraft were deployed to Pleiku Air Base and flew combat mission through Dec. 2. The remaining 18 aircraft remained at Bien Hoa Air Base and flew normal (Phase III) combat strike missions.

The 604th ACS flew about 5,000 training and combat sorties during the five phases of the Combat Dragon project. During Phase III each aircraft averaged between three and four missions every two days. During Phase IV, the maximum sortie rate reached 6.3 missions per day per aircraft. During Phase V, three new missions were flown: Forward Air Control, armed reconnaissance and night interdiction. In addition to missions with South Vietnam, Phase V missions were flown in southeast Laos in the Tigerhound areas.

The operational test phases of the Combat Dragon project were concluded in early December 1967, and the evaluation team returned to the United States to finish data analysis and make recommendations. During combat operations, Combat Dragon A-37As flew 4,463 sorties and dropped over 19,000 pieces of ordnance during the 107 day evaluation period. The team found the maintenance requirements of the A-37A to be lower than expected. The size of the squadron was acceptable for Phase III sortie rates, but would have to be increased for higher rates (i.e. there weren't enough pilots, crew chiefs and maintenance personnel to support high sortie generation rates). The A-37A was dependable and easy to maintain, so logistics and supply issues were not a major concern. The A-37A was judged to be an effective ground attack aircraft in the South Vietnam and Tigerhound areas (combat radius to 240 nm maximum). The A-37A was also an adequate Close Air Support aircraft; however, the low wing and limited right aft quadrant visibility when an observer wasn't flying (normally only a pilot flew) in the cockpit's right seat. One major problem identified involved the lack of fuel quantity gauges for the wingtip tanks and external drop tanks carried. For long duration missions, the pilot ran a significant risk of running out of fuel. Overall, the A-37A was judged an effective weapons system and full scale production of the A-37B proceeded based in part on the recommendations of the Combat Dragon team.

The YA-37A was permanently retired to the National Museum of the United States Air Force in July 1970 and remains on display in the Modern Flight Gallery.
Type Number built/
converted Remarks
YA-38A 2 COIN Prototype
A-37A 39 Attack conversion of T-37B
A-37B 577 Improved A-37A


TECHNICAL NOTES:
Armament: One GAU-2/A 7.62mm Gatling gun, plus 6,000 lbs. (800 lbs. on each of the inboard pylons, 600 lbs. on the middle two pylons and 500 lbs. on the outboard pylon) of mixed ordnance on eight hardpoints, including additional gun pods, high-explosive bombs, fire bombs, rockets, grenades and/or missiles
Engines: Two General Electric J85-GE-17/A axial flow turbojets of 2,400 lbs. thrust each (engines had 2850 lbs. maximum thrust but were derated to 2,400 lbs. thrust for the A-37A)
Maximum speed: 407 knots at 17,000 ft., maximum power
Cruising speed: Approx. 300 knots
Range: 1,180 nautical miles with 846.7 gallons of fuel at 301 knots average in 3.96 hours at 12,130 lbs. takeoff weight
Combat radius: 129 nautical miles with 3,646 lb. payload at 258 knots avg. in 1.3 hours
Service ceiling: 43,980 ft., 500 fpm, combat weight, maximum thrust
Span: 38 ft. 5 in.
Length: 29 ft. 4 in.
Height: 9 ft. 6 in.
Weight: 13,500 lbs. gross weight
Crew: Two

Serial numbers: (YA-37A) 62-5950 and 62-5951; (A-37A) 67-14503 to 67-14541; (A-37B) 67-14776 to 67-14823; 67-22483 to 67-22491; 68-7911 to 68-7980; 68-10777 to 68-10827; 69-6334 to 69-6446; 70-1277 to 70-1312; 71-790 to 71-854; 71-858 to 71-873; 71-1409 to 71-1416; 73-1056 to 73-1115; 73-1654 to 73-1658; 74-998 to 74-1013; 74-1694 to 74-1723; 75-374 to 75-385; 75-410 to 75-417; 75-424 to 75-441; 75-669 to 75-680

CESSNA A-37B

The A-37B was an improved version of the A-37A. One improvement was the installation of fully rated J85 jet engines capable of producing 2,850 pounds of thrust at maximum power. The J85 engines fitted to the A model Dragonfly were derated to 2,400 pounds thrust maximum. Another major difference was the inclusion of an in flight refueling (IFR) system with the refueling probe fitted to the nose of the aircraft. The A-37B used the probe and drogue method of IFR rather than the boom and receptacle method normally used on USAF fixed wing aircraft. The increased thrust of the engines gave the aircraft a maximum gross takeoff weight of 14,000 pounds. The use of the IFR system allowed the aircraft to fly with a maximum gross weight of 15,000 pounds -- the aircraft would takeoff with a heavy load of ordnance and limited fuel, conduct an IFR, then proceed on its mission. Other changes included improvements in the gun system: a selectable firing rate of 3,000 or 6,000 rounds per minute; an upgraded optical gun site; a nose mounted gun camera; and a strike camera mounted in the lower center fuselage. The control system also had some improvements: redundant control cables to the rudder and elevators and aileron boost tabs.

Cessna built a total of 577 A-37Bs. The aircraft was used for a relatively short period by the USAF; however, many aircraft had long service lives flying for the Air Force Reserves and Air National Guard. The United States also supplied many aircraft to foreign countries including South Vietnam during the late 1960s and early 1970s. The 4532nd Combat Crew Training Squadron at England Air Force Base in Louisiana initially trained over 100 South Vietnamese Air Force pilots. Each VNAF student received 112 hours of ground instruction and 85 hours of flight training. After training was completed, the VNAF pilots returned to Vietnam to fly A-37s supplied under the U.S. Military Assistance Program. South Vietnam had 10 squadrons of A-37s at peak strength during the early 1970s.

Type Number built/
converted Remarks
YA-38A 2 COIN Prototype
A-37A 39 Attack conversion of T-37B
A-37B 577 Improved A-37A


TECHNICAL NOTES:
Armament: One GAU-2/A 7.62mm Gatling gun with 1,500 rounds of ammunition, plus 6,000 lbs. (800 lbs. on each of the inboard pylons, 600 lbs. on the middle two pylons and 500 lbs. on the outboard pylon) of mixed ordnance on eight hardpoints, including additional gun pods, high-explosive bombs, fire bombs, rockets, grenades and/or missiles (note that the aircraft rarely flew with more than 4,000 lbs. of ordnance)
Engines: Two General Electric J85-GE-17/A axial flow turbojets of 2,850 lbs. thrust each
Maximum speed: 416 knots at 15,500 ft., maximum power
Cruising speed: Approx. 260 knots
Range: 808 nautical miles with 847 gallons of fuel at 257 knots average in 3.14 hours at 12,736 lbs. takeoff weight
Combat radius: 140 nautical miles with 3,152 lbs. payload at 259 knots avg. in 1.38 hours
Service ceiling: 25,000 ft. operational limit (cockpit not pressurized)
Span: 38 ft. 5 in.
Length: 29 ft. 4 in. (31 ft. 10 in. including refueling boom)
Height: 9 ft. 6 in.
Weight: 14,000 lbs. gross weight (15,024 lbs. after in flight refueling)
Crew: Two (usually flown with just a pilot in the left seat)

Serial numbers: (YA-37A) 62-5950 and 62-5951; (A-37A) 67-14503 to 67-14541; (A-37B) 67-14776 to 67-14823; 67-22483 to 67-22491; 68-7911 to 68-7980; 68-10777 to 68-10827; 69-6334 to 69-6446; 70-1277 to 70-1312; 71-790 to 71-854; 71-858 to 71-873; 71-1409 to 71-1416; 73-1056 to 73-1115; 73-1654 to 73-1658; 74-998 to 74-1013; 74-1694 to 74-1723; 75-374 to 75-385; 75-410 to 75-417; 75-424 to 75-441; 75-669 to 75-680

UH-1 Iroquois Bell

UH-1C "Huey".

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The Bell Helicopter Textron UH-1 Iroquois, commonly (or officially in the United States Marine Corps) known as the "Huey", is a multipurpose military helicopter, famous for its use in the Vietnam War. The "U" stands for utility, in contrast to attack or cargo helicopters.


The UH-1 was developed from 1955 US Army trials with the Bell Model 204. The initial designation of HU-1 (helicopter utility) led to its nickname, Huey. It was first used by the military in 1959 and went into tri-service production in 1962 as the UH-1. The last were produced in 1976 with more than 16,000 made in total, of which about 7,000 saw use during the Vietnam War.


In Vietnam, 2,202 Huey pilots were killed and approximately 2,500 aircraft were lost, roughly half to combat and the rest to operational accidents.



Specifications (UH-1D)



General characteristics


• Crew: 1-4


• Capacity: 3,880 lb including 14 troops, or 6 stretchers, or equivalent cargo


• Length: 57 ft 1 in with rotors (17.4 m)


• Fuselage width: 8 ft 7 in (2.6 m)


• Rotor diameter: 48 ft 0 in (14.6 m)


• Height: 14 ft 5 in (4.4 m)


• Empty weight: 5,215 lb (2,365 kg)


• Loaded weight: 9,040 lb (4,100 kg)


• Max takeoff weight: 9,500 lb (4,310 kg)


• Powerplant: 1× Lycoming T53-L-11 turboshaft, 1,100 shp (820 kW)


Performance


• Maximum speed: 135 mph (220 km/h)


• Cruise speed: 125 mph (205 km/h)


• Range: 315 mi (510 km)


• Service ceiling: 19,390 ft (Dependent on environmental factors such as weight, outside temp., etc) (5,910 m)


• Rate of climb: 1,755 ft/min (8.9 m/s)


• Power/mass: 0.15 hp/lb (0.25 kW/kg)


Armament


Variable, but may include a combination of:


• 2x 7.62 mm M60 machine gun, or 2x 7.62 mm GAU-17/A machine gun


• 2x 7-round or 19-round 2.75 in (70 mm) rocket pods


• 2x 7.62 mm Rheinmetall MG3 (German Army and German Luftwaffe)


For information on US armament systems see:


Main article: U.S. Helicopter Armament Subsystems



________________________________________

Sources:

Wikipedia: UH-1 Iroquois "Huey"

H-54 Tarhe Sikorsky

The CH-54 Tarhe is a twin-engine heavy-lift helicopter designed by Sikorsky Aircraft for the United States Army. It is named after Tarhe (whose nickname was "The Crane"), an eighteenth-century chief of the Wyandot Native American tribe. The civil version is the S-64 Skycrane.
________________________________________
Type: Heavy Lift Helicopter
Crew: 3
Manufacturer: Sikorsky
Models: see variants

Maiden flight: 1962
Service Delivery: N/A
Number built: 105
________________________________________
Specifications: CH-54B Tarhe
Powerplant:
Model: ratt & Whitney T73-P-700
Type: Turboshaft
Number: Two
Horsepower: 4,800 shp each
________________________________________
Dimensions:
Length: 88 ft 6 in (26.97 m)
Rotor Diameter: 72 ft 0 in (21.95 m)
Height: 25 ft 5 in (7.75 m)
Disc area: 4071.5 ft² (378.24 m²)

Weights:
Empty: 19,800 lb (8,980 kg)
Max takeoff: 47,000 lb (21,000 kg)
Payload: 20,000 lb (9,000 kg)
Performance:
Maximum speed: 150 mph (240 kph)
Cruise speed: 115 mph (185 kph)
Range: 230 mi (370 km)
Service ceiling: 18,330 ft (5,600 m)
Rate of climb: 1,330 ft/min (6.75 m/s)
________________________________________
Development:
The first flight of the turboshaft-powered S-64 Skycrane was May 9, 1962, with the U.S. Army eventually purchasing 105, designating them CH-54. Used in Vietnam for transport and downed-aircraft retrieval, it was highly successful, thanks to the 'adaptable' nature of the module system first conceived by General James M. Gavin in his book Airborne Warfare in 1947. Early pods could not carry troops and external sling-loads at the same time. Advanced pods for the CH-54 could carry troops and cargo underslung at the same time but were not purchased. The Skycrane can not only hold its cargo up and tight against its center spine to lessen drag and eliminate the pendulum effect when flying forward, it can winch vehicles up and down from a hovering position, so the helicopter itself need not land.. Due to budget cuts the HLH program was cancelled and the CH-54s not upgraded with larger engines. Boeing CH-47 Chinook gradually supplemented it in combat, although Skycranes remained in U.S. National Guard service until the early 1990s. The Soviet Union also created much larger crane helicopters with a similar skeletal design.
Today, Erickson Air-Crane of Central Point, Oregon operates the largest fleet of S-64 helicopters in the world under the name Erickson S-64 Aircrane, which can be equipped with water-bombing equipment for firefighting duties worldwide. After obtaining the type certificate and manufacturing rights in 1992, Erickson remains the manufacturer and world’s largest operator of S-64s.
Variants:
YCH-54A: Pre-production aircraft, six built.
CH-54A: Production model powered by two 4500shp T-73-P1 turboshafts, 54 built.
CH-54B: Heavier version of the CH-54A with two 4800 shp T-73-P700 turboshafts and twin-wheeled main undercarriage, 37 built.
________________________________________
Sources:
Wikipedia: H-54 Tarhe

H-47 Chinook Boeing-Vertol

The Boeing CH-47 Chinook is a versatile, twin-engine, tandem rotor heavy-lift helicopter. Its top speed of 170 knots (196 mph, 315 km/h) was faster than utility and attack helicopters of the 1960s and even many of today. Its primary roles include troop movement, artillery emplacement and battlefield resupply. There is a wide loading ramp at the rear of the fuselage and three external-cargo hooks.
Chinooks have been sold to 16 nations; the largest users are the U.S. Army and the Royal Air Force. The H-47 is now produced by Boeing Integrated Defense Systems.
________________________________________
Type: Cargo helicopter
Crew: 3 (pilot, copilot, flight engineer)
Capacity:
– 33-55 troops or
– 24 litters and 3 attendants or
– 28,000 pounds cargo

Manufacturer: Boeing-Vertol Helicopters
Maiden flight: Sept. 21, 1961
Service Delivery: 1962
Number built: 1,000+
________________________________________
Specifications: CH-47D
Powerplant:
Model: Lycoming T55-GA-712
Type: Turboshaft
Number: Two
Horsepower: 3,750 hp
Dimesions:
Length: 98 ft 10 in (30.1 m)
Rotor diameter: 60 ft 0 in (18.3 m)
Height: 18 ft 11 in (5.7 m)
Disc area: 2,800 ft² (260 m²)
Weights:
Empty: 23,400 lb (10,185 kg)
Loaded: 26,680 lb (12,100 kg)
Max takeoff: 50,000 lb (22,680 kg)

Performance:
Maximum speed: 170 knots (196 mph, 315 km/h)
Cruise speed: 130 kt (137 mph, 220 km/h)
Range: 400 nmi (450 mi, 741 km)
Service ceiling: 18,500 ft (5,640 m)
Rate of climb: 1,522 ft/min (10.1 m/s)
Disc loading: 9.5 lb/ft² (47 kg/m²)
Power/mass: 0.28 hp/lb (460 W/kg)
________________________________________
Armament
M-134 7.62 minigun,
M-240 7.62 machine gun
________________________________________
Sources:
Wikipedia: H-47 Chinook

H-46 Sea Knight Vertol

The Vertol (later Boeing) CH-46 Sea Knight is a medium-lift tandem rotor cargo helicopter, used by the United States Marine Corps (USMC) to provide all-weather, day-or-night assault transport of combat troops, supplies and equipment. Assault Support is its primary function, and the movement of supplies and equipment is secondary. Additional tasks include combat support, search and rescue, support for forward refueling and rearming points, CASEVAC and Tactical Recovery of Aircraft and Personnel (TRAP).
________________________________________
Type: Cargo helicopter
Crew: 4 (2 pilots, 1 crew chief, 1 gunner)
Capacity: 25 Troops
Manufacturer: Vertol Aircraft Corp.

Models: See variants
Maiden flight: Aug. 1962
Service Delivery: 1964
Number built: 600+
________________________________________
Specifications:
Powerplant:
Model: General Electric T58-GE-16
Type: Turboshaft
Number: Two
Horsepower: 1,870 shp
________________________________________
Dimensions:
Length: 45 ft 8 in fuselage (13.92 m)
Fuselage width: 7 ft 3 in (2.2 m)
Rotor Diameter: 51 ft (16 m)
Disc Area: 4,100 ft² (380 m²)
Height: 16 ft 8.5 in (5.1 m)
Weights:
Empty: 15,537 lb (7,047 kg)
Loaded: 17,396 lb (7,891 kg)
Max takeoff: 24,300 lb (11,000 kg)

Performance:
Maximum speed: 165 mph (265 kph)
Combat Radius: 420 mi (676 km)
Ferry Range: 420 mi (676 km)
Service ceiling: 14,000 ft (4,300 m)
Rate of climb: 2,045 ft/min (10.4 m/s)
Disc loading: 4.2 lb/ft² (21 kg/m²)
Power/mass: 0.215 hp/lb (354 W/kg)
________________________________________
Armament:
2×XM218 .50 BMG machine guns
1 Ramp mounted M240G 7.62mm MG
________________________________________

________________________________________
Sources:
Wikipedia: H-46 Sea Knight

H-34 Choctaw Sikorsky

The Sikorsky H-34 Choctaw (also known as the Sikorsky S-58) was a military helicopter originally designed for the US Navy for service in the anti-submarine warfare (ASW) role.
________________________________________
Type: Cargo helicopter
Crew: 2
Capacity: 16 troops or 8 stretchers
Manufacturer: Sikorsky Aircraft

Models: See variants
Maiden flight: March 8, 1954
Service Retirement: N/A
Number built: N/A
________________________________________
Specifications: CH-21C Shawnee
Powerplant:
Model: R-1820-84
Type: Radial Engine
Number: One
Horsepower: N/A
________________________________________
Dimensions:
Length: 56 ft 8.5 in (17.28 m)
Rotor Diameter: 56 ft 0 in (17.07 m)
Disc Area: 2463 ft² (228.85 m²)
Height: 15 ft 11 in (4.85 m)
Weights:
Empty: 7,900 lb (3,583 kg)
Max takeoff: 14,000 lb (6,350 kg)

Performance:
Maximum speed: 123 mph (198 kph)
Range: 182 mi (293 km)
Service ceiling: N/A
Rate of climb: N/A
________________________________________
Armament:
Normally none
________________________________________
Development:
The Sikorsky S-58 was developed from the Sikorsky's UH-19 Chickasaw. The aircraft first flew on March 8, 1954. It was initially designated HSS-1 Seabat (in its anti-submarine configuration) and HUS-1 Seahorse (in its utility transport configuration) under the US Navy designation system. Under the US Army's system, also used by the fledgling US Air Force, the helicopter was designated H-34. The US Army applied the name Choctaw to the helicopter. In 1962, under the new unified system, the Seabat was redesignated SH-34, the Seahorse as the UH-34, and the Choctaw as the CH-34.
Roles included utility transport, anti-submarine warfare, search and rescue, and VIP transport. In it standard configuration transport versions could carry 12 to 16 troops, or eight stretcher cases if utilized in the MedEvac role, while VIP transports carried significantly fewer people in significantly greater comfort.
135 H-34 were built in the US and assembled by Sud-Aviation in France, 166 were produced under licence in France by Sud-Aviation for the French Air Force, Navy and Army Aviation (ALAT).
The CH-34 was also built and developed under license from 1958 in the United Kingdom by Westland Aircraft as the turbine engined Wessex which was used by the Royal Navy. The RN Wessex was fitted out with weapons and ASW equipment for use in an antisubmarine role. The RAF used the Wessex, with turboshaft engines, as an air/sea rescue helicopter and as troop transporter. Wessexes were also exported to other countries and produced for civilian use.
________________________________________
Sources:
Wikipedia: H-34 Choctaw

H-21 Shawnee Piasecki

________________________________________

CH-21C Shawnee transporting M101 105mm howitzer.
________________________________________
The Piasecki H-21 Workhorse/Shawnee is an American helicopter, the fourth of a line of tandem rotor helicopters designed and built by Piasecki Helicopter (later Boeing Vertol). Commonly called the "flying banana", it was a multi-mission helicopter, utilizing wheels, skis, or floats. It was used for Arctic rescue because it performed so well at low temperatures.
________________________________________
Type: Cargo helicopter
Crew: 2
Capacity: 22 troops or 12 stretchers
Manufacturer: Piasecki Helicopter

Models: See variants
Maiden flight: 1949
Service Retirement: 1967
Number built: N/A
________________________________________
Specifications: CH-21C Shawnee
Powerplant:
Model: Wright R-1820-103
Type: Radial Engine
Number: One
Horsepower: 1,425 hp
________________________________________
Dimensions:
Length: 52 ft 6 in (16.0 m)
Rotor Diameter: 44 ft 0 in (13.4 m)
Disc Area: 3,041 ft² (282.7 m²)
Height: 15 ft 9 in (4.80 m)
Weights:
Empty: 8,950 lb (4,058 kg)
Max takeoff: 15,200 lb (6,893 kg)

Performance:
Maximum speed: 127 mph (204 kph)
Range: 265 mi (426 km)
Service ceiling: 9,450 ft (2,880 m)
Rate of climb: N/A
Disc loading: 5 lb/ft² (24 kg/m²)
Power/mass: 0.09 hp/lb (150 W/kg)
________________________________________
Armament:
Usually twin or quad .50 machine guns
________________________________________
Design and Development:
Piasecki Helicopter designed and successfully sold to the US Navy a series of tandem rotor helicopters, starting with the HRP-1 of 1944. The HRP-1 was nicknamed the "flying banana" because of the upward angle of the aft fuselage that ensured the large rotors did not hit each other in flight. The name would later be applied to other Piasecki helicopters of similar design, including the H-21. In 1949, Piasecki provided the H-21 Workhorse to the USAF, which was an improved, all-metal derivative of the HRP-1.
________________________________________
Sources:
Wikipedia: H-21 Shawnee

H-19 Chickasaw Sikorsky

The Sikorsky H-19, (also known as the S-55) was a multi-purpose helicopter used by the United States Army. It was also license-built by Westland Aircraft as the Westland Whirlwind in the United Kingdom. United States Navy and Coast Guard models were designated HO4S, while those of the U.S. Marine Corps were HRS.
________________________________________
Type: Utility Helicopter
Crew: 2 (pilot, copilot)
Capacity: 12 troops or 8 litters
Manufacturer: Sikorsky

Models: see variants
Maiden flight: Nov. 10, 1949
Service Delivery: 1950
Number built: 1,550+
________________________________________
Specifications:
Powerplant:
Model: Pratt & Whitney R-1340-57
Type: Radial Engine
Number: One
Horsepower: 600 hp
________________________________________
Dimensions:
Length: 62 ft 7 in (19.1 m)
Rotor Diameter: 53 ft (16.16 m)
Height: 13 ft 4 in (4.07 m)

Weights:
Empty: 4,795 lb (2,177 kg)
Loaded: 7,200 lb (3,266 kg)
Max takeoff: 7,900 lb (3,587 kg)
Performance:
Maximum speed: 101 mph (163 km/h)
Range: 405 mi (652 km)
Service ceiling: 10,500 ft (3,200 m)
Rate of climb: 700 ft/min (213 m/min)
________________________________________
Design and Development:
The H-19's first flight was on November 10, 1949 and it entered operations in 1950. Over 1,000 of the helicopters were manufactured by Sikorsky for the United States. An additional 550 were manufactured by licensees of the helicopter including Westland Aircraft, Sud-Est in France and Mitsubishi in Japan.
The helicopter was widely exported, used by many other nations, including Greece, Israel, Chile, South Africa, Denmark and Turkey.
________________________________________
Sources:
Wikipedia: Sikorsky H-19

HH-3E Jolly Green Giant Sikorsky

The Sikorsky S-61R is a developed version of the S-61/SH-3 Sea King, which was also built under license by Agusta as the AS-61R. The S-61R served in the United States Air Force as the CH-3C/E Sea King and the HH-3E Jolly Green Giant, and with the United States Coast Guard as the HH-3F "Pelican".

--------------------------------------------------------------------------------

Sources:
Wikipedia: Sikorsky S-61R
Sikorsky HH-3E Jolly Green Giant
________________________________________

________________________________________
The Sikorsky S-61R is a developed version of the S-61/SH-3 Sea King, which was also built under license by Agusta as the AS-61R. The S-61R served in the United States Air Force as the CH-3C/E Sea King and the HH-3E Jolly Green Giant, and with the United States Coast Guard as the HH-3F "Pelican".
________________________________________
Sources:
Wikipedia: Sikorsky S-61R

Sikorsky S-61R
From Wikipedia, the free encyclopedia
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S-61R/CH-3C/E
HH-3E Jolly Green Giant
HH-3F "Pelican"

US Coast Guard HH-3F "Pelican"
Role
Medium-lift transport/SAR helicopter
Manufacturer
Sikorsky
Agusta
First flight
1959
Introduction
1961
Status
Active service
Primary users
United States Air Force
United States Coast Guard
Italian Air Force
Developed from
SH-3 Sea King
The Sikorsky S-61R is a twin-engine helicopter used in transport or search and rescue roles. A developed version of the S-61/SH-3 Sea King, the S-61R was also built under license by Agusta as the AS-61R. The S-61R served in the United States Air Force as the CH-3C/E Sea King and the HH-3E Jolly Green Giant, and with the United States Coast Guard as the HH-3F "Pelican".[1]
The Sikorsky S-61R was developed as a derivative of their S-61/SH-3 Sea King model. It features a substantially-revised fuselage with a rear loading ramp, a conventional though water-tight hull instead of the S-61's boat-hull, and retractable tricycle landing gear. The fuselage layout was used by Sikorsky for the larger CH-53 variants, and by the much later (though similarly-sized) S-92.
Sikorsky designed and built a S-61R prototype as a private venture with its first flight in 1963. During its development, the US Air Force placed an order for the aircraft, which was designated CH-3C. The Air Force used the CH-3C to recover downed pilots. The CH-3E variant with more powerful engines would follow in 1965.[2]


A USAF HH-3E Jolly Green Giant helicopter flies over Canada.
The improved HH-3E variant would follow later, with eight built, and all CH-3Es converted to this standard.[3] Known as the Jolly Green Giant, the HH-3E featured protective armor, self-sealing tanks, a retractable inflight refueling probe, jettisonable external tanks, a high-speed hoist, and other specialized equipment.[3]
In 1965, U.S. Coast Guard ordered a version designated, HH-3F Sea King (more commonly known by its nickname "Pelican") for all-weather air-sea rescue.[2] The Pelican featured a search radar with a nose antenna radome offset to port,[1][3] and water landing capability.[2]
Italian Agusta built a S-61R variant, named AS-61R under license. Agusta produced 22 helicopters for the Italian Air Force.[2] The company claimed it could re-open the production line in 36 months to build additional AS-61 helicopters.[4]
Specifications (HH-3E)

Data from Evergreen,[10] Globalsecurity[11]
General characteristics
• Crew: 3
• Capacity: 28 passengers
• Length: 73 ft (22.3 m)
• Rotor diameter: 62 ft (18.9 m)
• Height: 18 ft 1 in (5.51 m)
• Empty weight: 13,341 lb (6,051 kg)
• Max takeoff weight: 22,050 lb (10,000 kg)
• Powerplant: 2× General Electric T58-10 turboshafts, 1,500 hp (1,119 kW) each
• Rotor system: 5 blades
Performance
• Maximum speed: 143 kn (165 mph, 265 km/h)
• Range: 779 mi (677 NM, 1,254 km)
• Service ceiling: 17,500 or 21,000? ft (5,334 m or 6,400 m)
• Rate of climb: 1,310-2,220? ft/min (400-670? m/min)
• Disc loading: 6,500 lb (2,948 kg)
• Fuel: 683 US gal (2,585 L)
Armament
• Various equipment particular to the operating country.
• Door guns on some variants (For information on American equipment, see U.S. Helicopter Armament Subsystems, S-61R)

AH-1 Cobra Bell

The AH-1 Cobra is an attack helicopter manufactured by Bell. It shares a common engine, transmission and rotor system with the older UH-1 Iroquois (nicknamed "Huey"). The AH-1 is also sometimes referred to as the "HueyCobra" or "Snake".
The AH-1 was once the backbone of the United States Army's attack helicopter fleet, but has been replaced by the AH-64 Apache in Army service. Upgraded versions continue to fly with several other users. The AH-1 twin engine versions remain in service with United States Marine Corps as the service's primary attack helicopter.
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Type: Attack Helicopter
Crew: 2 (pilot, copilot/gunner)
Manufacturer: Bell Helicopter Textron
Models: see variants
Maiden flight: Sept. 07, 1965

Service Delivery: 1967
Number built: 1,116+
Primary Users: U.S. Army, Japan Self Defense Forces, Republic of Korea Army, Israeli Air Force
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Specifications:
– AH-1G HueyCobra
– AH-1F "Modernized" HueyCobra
– AH-1J SeaCobra
– AH-1W Super Cobra
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Sources:
Wikipedia: AH-1 Cobra

F-105 Thunderchief Republic

Republic YF-105A (S/N 54-0098, the first of two prototypes). (U.S. Air Force photo)
The Republic F-105 Thunderchief, was a single-seat supersonic fighter-bomber used by the United States Air Force. The Mach 2 capable F-105 bore the brunt of strike bombing over North Vietnam during the early years of the Vietnam War. A two-seat Wild Weasel version was later used in the specialized SEAD role of suppressing surface-to-air missile sites. It was commonly known as the "Thud" by its crews.
As a follow-on to the Mach 1 capable F-100, the F-105 was also armed with missiles and a cannon; however, its design was tailored to high-speed low-altitude penetration carrying a single nuclear bomb internally. First flown in 1955, the Thunderchief entered service in 1958. As the largest single-engined fighter ever employed by the USAF, the single-seat F-105 would be adapted to deliver a greater iron bomb load than the four-engined ten-man strategic bombers of World War II. The F-105 would be best remembered as the primary strike bomber over North Vietnam in the early stages of the Vietnam War. Over 20,000 Thunderchief sorties were flown, with 382 aircraft lost (nearly half of the 833 produced) including 62 operational casualties. Although it lacked the agility of the smaller MiG fighters, USAF F-105s demonstrated the effectiveness of guns, and were credited with downing 27.5 enemy aircraft.
During the war, the two-seat F-105F and F-105G Wild Weasel variants became the first dedicated Suppression of Enemy Air Defenses (SEAD) platforms, fighting against the Soviet-built S-75 Dvina (SA-2 Guideline) surface-to-air missiles. Two Wild Weasel pilots earned the Medal of Honor attacking missile sites, with one shooting down two MiG-17s the same day. The dangerous missions often required them to be the "first in, last out" in order to suppress the threat air defenses prior to strike aircraft arriving and keeping them suppressed until the strike aircraft left the area.

A two-seat F-105G Wild Weasel. (U.S. Air Force photo)
Although the F-105 weighed 50,000 pounds (22,680 kg), the aircraft could exceed the speed of sound at sea level and Mach 2 at high altitude. It could carry up to 14,000 pounds (6,700 kg) of bombs and missiles. The Thunderchief was later replaced as a strike aircraft over North Vietnam by both the F-4 Phantom II and the swing-wing F-111. However, the "Wild Weasel" variants remained in service until 1984, when they were replaced by a specialized F-4G "Wild Weasel V".
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Sources:
Wikipedia: F-105 Thunderchief

F-104 Starfighter Lockheed

Lockheed F-104 Starfighter was an American single-engined, high-performance, supersonic interceptor aircraft that was one of the Century Series of aircraft and served with the United States Air Force (USAF) from 1958 until 1967. It continued in service with Air National Guard units until it was phased out in 1975. The National Aeronautics and Space Administration (NASA) flew a small mixed fleet of F-104 types in support of supersonic flight tests and spaceflight programs until they were retired in 1994. Several two-seat trainer versions were produced, the most numerous being the TF-104G.
The F-104C was used in combat with the USAF during the Vietnam War, and F-104A aircraft were deployed by Pakistan during the Indo-Pakistani wars. Republic of China Air Force F-104s also engaged MiG-19s of the People's Liberation Army Air Force over the disputed island of Kinmen.
The poor safety record of the F-104 Starfighter brought the aircraft into the public eye, especially in Luftwaffe service, and the subsequent Lockheed bribery scandals surrounding the original purchase contracts caused considerable political controversy in Europe and Japan. A USAF study of other Century Series fighters revealed that the F-100 Super Sabre had an accident rate far worse than the F-104.
The F-104G version sold well amongst NATO air forces where these high-speed fighter-bomber variants continued in service with most operators until the late 1980s. Lockheed developed the final and most advanced version of the Starfighter, the F-104S, for use by the Italian Air Force which was designed to carry AIM-7 Sparrow missiles, the Italian Air Force being the last remaining Starfighter operator on retiring their fleet in 2004. Many F-104 users eventually replaced them with the F-16 or Panavia Tornado. A projected, highly-modified version of the F-104 known as the CL-1200 Lancer did not proceed and the project was cancelled at the mock-up stage. A civilian demonstration team based in Florida operates the last three airworthy Starfighters.
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Type: Interceptor & fighter-bomber
Crew: 1
Manufacturer: Lockheed Aircraft
Models: see variants

Maiden flight: March 4, 1954
Service Delivery: Feb. 20, 1958
Number built: 2,578
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Specifications: F-104G
Powerplant:
Model: General Electric J79-GE-11A
Type: afterburning turbojet
Number: One
Dry thrust: 10,000 lbf (48 kN)
Thrust with afterburner: 15,600 lbf (69 kN)
Dimesions:
Length: 54 ft 8 in (16.66 m)
Wingspan: 21 ft 9 in (6.36 m)
Height: 13 ft 6 in (4.09 m)
Wing area: 196.1 sq ft (18.22 m²)
Airfoil: Biconvex 3.36% root and tip
Zero-lift drag coefficient: 0.0172
Drag area: 3.37 sq ft (0.31 m²)
Aspect ratio: 2.45
Weights:
Empty: 14,000 lb (6,350 kg)
Loaded: 20,640 lb (9,365 kg)
Max takeoff: 29,027 lb (13,170 kg)

Performance:
Maximum speed: 1,328 mph (1,154 knots, 2,125 km/h)
Combat radius: 420 mi (365 NM, 670 km)
Ferry range: 1,630 mi (1,420 nm, 2,623 km)
Service ceiling: 50,000 ft (15,000 m)
Rate of climb: 48,000 ft/min (244 m/s)
Wing loading: 105 lb/sq ft (514 kg/m²)
Thrust/weight: 0.54 with max. takeoff weight (0.76 loaded)
Lift-to-drag ratio: 9.2
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Armament
1× 20 mm (0.787 in) M61 Vulcan cannon
– ammunition: 725 rounds
Hardpoints:
7 with a capacity of 4,000 lb (1,800 kg)
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Sources:
Wikipedia: F-104 Starfighter

F-101 Voodoo McDonnell

The McDonnell F-101 Voodoo was a supersonic military fighter flown by the USAF and the RCAF. Initially designed as a long-range bomber escort (known as a penetration fighter) for the Strategic Air Command, the Voodoo served in a variety of other roles, including the fighter bomber, all-weather interceptor aircraft and photo reconnaissance roles.
Reconnaissance Voodoos were instrumental during the Cuban Missile Crisis and saw extensive service during the Vietnam War.
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Type: Fighter
Crew: 2
Manufacturer: McDonnell Aircraft
Models: see variants
Number built: 885

Maiden flight: Sept. 29, 1954
Service Delivery: May 1957
Retired (USAF): 1966
Retired (US ANG): 1982
Retired (RCAF/CAF): 1984
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Specifications: F-101B Voodoo
Powerplant:
Model: Pratt & Whitney J57-P-55
Type: After-burning Turbojet
Number: Two
Dry Thrust: 11,990 lb
W. Afterburner: 16,900 lb
Fuel:
Internal Capacity: 2,053 US gal (7,771 L)
Capacity with 2 external tanks:
– 2,953 US gal (11,178 L)
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Dimensions:
Length: 67 ft 5 in (20.55 m)
Wingspan: 39 ft 8 in (12.09 m)
Height: 18 ft 0 in (5.49 m)
Wing area: 368 ft² (34.20 m²)
Airfoil:
NACA 65A007 mod root
NACA 65A006 mod tip
Wing loading: 124 lb/ft² (607 kg/m²)
Thrust/weight: 0.74

Weights:
Empty: 28,495 lb (12,925 kg)
Loaded: 45,665 lb (20,715 kg)
Max takeoff: 52,400 lb (23,770 kg)
Performance:
Maximum speed:
– 1,134 mph (1,825 kph) at 35,000 ft
Range: 1,520 mi (2,450 km)
Service ceiling: 58,400 ft (17,800 m)
Rate of climb: 49,200 ft/min (250 m/s)
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Bombload:
– Four missiles
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Sources:
Wikipedia: F-101 Voodoo

F-100 Super Sabre North American

The North American F-100 Super Sabre was a jet fighter aircraft that served with the United States Air Force (USAF) from 1954 to 1971 and with the Air National Guard (ANG) until 1979. As the first of the Century Series collection of USAF jet fighters, it was the first of a series of US fighters capable of supersonic speed in level flight and made extensive use of titanium throughout the aircraft.
The F-100 was designed originally as a higher performance follow-on to the F-86 air superiority fighter. Adapted as a fighter bomber, the F-100 would be supplanted by the Mach 2 class F-105 Thunderchief for strike missions over North Vietnam. The F-100 flew extensively over South Vietnam as the Air Force's primary close air support jet until replaced by the more efficient subsonic A-7 Corsair II The F-100 also served in several NATO air forces and with other US allies. In its later life, it was often referred to as "the Hun," a shortened version of "one hundred."
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Type: Fighter-bomber
Crew: 1
Manufacturer: North American Aviation
Models: see variants
Number built: 2,294
Primary Users: United States Air Force France, Denmark, Turkey, Taiwan

Maiden flight: May 25, 1953
Service Delivery: Sept. 27, 1954
Retired (USAF): 1970
Retired (US ANG): 1979
Retired (Turkey): 1982
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Specifications: F-100D Super Sabre
Powerplant:
Model: Pratt & Whitney J57-P-21/21A
Type: After-burning Turbojet
Number: One
Dry Thrust: 10,200 lb
W. Afterburner: 16,000 lb
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Dimensions:
Length: 50 ft (15.2 m)
Wingspan: 38 ft 9 in (11.81 m)
Height: 16 ft 2¾ in (4.95 m)
Wing area: 400 ft² (37 m²)
Wing loading: 72.1 lb/ft² (352 kg/m²)
Thrust/weight: 0.55
Lift-to-drag ratio: 13.9

Weights:
Empty: 21,000 lb (9,500 kg)
Loaded: 28,847 lb (13,085 kg)
Max takeoff: 34,832 lb (15,800 kg)
Performance:
Maximum speed: 864 mph (1,390 kph)
Range: 1,995 mi (3,210 km)
Service ceiling: 50,000 ft (15,000 m)
Rate of climb: 22,400 ft/min (114 m/s)
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Armament:
– 4× 20 mm M39 cannon
Bombload:
– 7,040 lb (3,190 kg) of bombs
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Sources:
Wikipedia: F-100 Super Sabre

F-8 Crusader Vought

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The F-8 Crusader (originally F8U) was a single-engine aircraft carrier-based fighter aircraft built by Chance-Vought of Dallas, Texas, USA. It replaced the Vought F-7 Cutlass. The first F-8 prototype was ready for flight in February 1955, and was the last American fighter with guns as the primary weapon. The RF-8 Crusader was a photo-reconnaissance development and operated longer in U.S. service than any of the fighter versions. RF-8s played a crucial role in the Cuban Missile Crisis, providing essential low-level photographs impossible to acquire by other means. Naval Reserve units continued to operate the RF-8 until 1987.
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Type: Carrier based Fighter
Crew: 1
Manufacturer: Chance-Vought
Models: see variants
Number built: 1,261

Maiden flight: MArch 25, 1955
Service Delivery: March 1957
Retired: Dec. 19, 1999
Primary Users: U.S. Navy, U.S. Marine Corps, French Navy, Philippines
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Specifications: F-8E Crusader
Powerplant:
Model: Pratt & Whitney J57-P-20A
Type: After-burning Turbojet
Number: One
Dry Thrust: 10,700 lb
W. Afterburner: 18,000 lb
Fuel (Internal): 1,325 U.S. gal (5,102 L)
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Dimensions:
Length: 54 ft 3 in (16.53 m)
Wingspan: 35 ft 8 in (10.87 m)
Height: 15 ft 9 in (4.80 m)
Wing area: 375 ft² (34.8 m²)
Airfoil:
NACA 65A006 mod root
NACA 65A005 mod tip
Wing loading: 77.3 lb/ft² (377.6 kg/m²)
Thrust/weight: 0.62

Weights:
Empty: 17,541 lb (7,956 kg)
Loaded: 29,000 lb (13,000 kg)
Performance:
Maximum speed:
– 1,225 mph (1,975 kph) at 36,000 ft
Cruise speed: 570 mph (495 kn, 915 kph)
Combat Radius: 450 mi (730 km)
Ferry Range: 1,735 mi (2,795 km)
Service ceiling: 58,000 ft (17,700 m)
Rate of climb: 31,950 ft/min (162.3 m/s)
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Armament:
– 4× 20 mm Colt Mk 12 cannons in lower fuselage
— 125 rounds/gun
Bombload:
– 5,000 lb (2,300 kg)
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Sources:
Wikipedia: F-8 Crusader

F-4 Phantom II McDonnell Douglas

The McDonnell Douglas F-4 Phantom II is a two-seat, twin-engined supersonic long-range all-weather fighter-bomber originally developed for the U.S. Navy by McDonnell Aircraft.


The Phantom remained in production from 1958 to 1981, with a total of 5,195 built, and was used by the U.S. military from 1960 to 1996, serving with the U.S. Air Force, Marine Corps, and the US Navy. It was used extensively by all three U.S. services operating in Vietnam, ending the war as the principal air superiority fighter for both the Navy and Air Force, as well as being important in the ground-attack and reconnaissance roles.

The Phantom continued to form a major part of U.S. military air power throughout the 1970s and 80s, being gradually replaced by more modern aircraft such as the F-15 Eagle and F-16 Fighting Falcon in the U.S. Air Force and the F-14 Tomcat and F/A-18 Hornet in the U.S. Navy. It remained in service in the reconnaissance and Wild Weasel roles in the 1991 Gulf War.

The Phantom was also operated by the armed forces of 11 other nations. Israeli Phantoms saw extensive combat in numerous Arab–Israeli conflicts, while Iran used its large fleet of Phantoms in the Iran–Iraq War. Phantoms remain in front line service with seven countries, and in use as an unmanned target in the U.S. Air Force.

Overview

The F-4 Phantom was designed as a fleet defense fighter for the U.S. Navy, and first entered service in 1960. By 1963, it had been adopted by the U.S. Air Force for the fighter-bomber role. When production ended in 1981, 5,195 Phantom IIs had been built, making it the most numerous American supersonic military aircraft. Until the advent of the F-15 Eagle, the F-4 also held a record for the longest continuous production with a run of 24 years. Innovations in the F-4 included an advanced pulse-doppler radar and extensive use of titanium in its airframe.

Despite the imposing dimensions and a maximum takeoff weight of over 60,000 pounds (27,000 kg), the F-4 had a top speed of Mach 2.23 and an initial climb of over 41,000 ft per minute (210 m/s). Shortly after its introduction, the Phantom set 15 world records, including an absolute speed record of 1,606.342 mph (2,585.086 km/h), and an absolute altitude record of 98,557 ft (30,040 m). Although set in 1959–1962, five of the speed records were not broken until 1975 until the F-15 eagle came into service.

The F-4 could carry up to 18,650 pounds (8,480 kg) of weapons on nine external hardpoints, including air-to-air and air-to-ground missiles, and unguided, guided, and nuclear bombs. Since the F-8 Crusader was to be used for close combat, the F-4 was designed, like other interceptors of the day, without an internal cannon; In a dogfight, the RIO or WSO (commonly called "backseater" or "pitter") assisted in spotting opposing fighters, visually as well as on radar. It became the primary fighter-bomber of both the Navy and Air Force by the end of the Vietnam War.

Due to its distinctive appearance and widespread service with United States military and its allies, the F-4 is one of the best-known icons of the Cold War. It served in the Vietnam War and Arab–Israeli conflicts, with American F-4 crews achieving 277 aerial victories in South East Asia and completing countless ground attack sorties.

The F-4 Phantom has the distinction of being the last United States fighter to attain ace status in the 20th century. During the Vietnam War, the USAF had one pilot and two WSOs, and the USN one pilot and one RIO, become aces in air-to-air combat. It was also a capable tactical reconnaissance and Wild Weasel (suppression of enemy air defenses) platform, seeing action as late as 1991, during Operation Desert Storm.

The F-4 Phantom II was also the only aircraft used by both of the USA's flight demonstration teams. The USAF Thunderbirds (F-4E) and the USN Blue Angels (F-4J) both switched to the Phantom for the 1969 season; the Thunderbirds flew it for five seasons, the Blue Angels for six.



The baseline performance of a Mach 2-class fighter with long range and a bomber-sized payload would be the template for the next generation of large and light/middle-weight fighters optimized for daylight air combat. The Phantom would be replaced by the F-15 Eagle and F-16 Fighting Falcon in the U.S. Air Force. In the U.S. Navy, it would be replaced by the F-14 Tomcat and the F/A-18 Hornet which revived the concept of a dual-role attack fighter.



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Sources:
Wikipedia: F-4 Phantom II

C-130 Hercules Lockheed

The Lockheed C-130 Hercules is an four-engine turboprop military transport aircraft built by Lockheed and the main tactical airlifter for many military forces worldwide. Over 40 models and variants of the Hercules serve with more than 50 nations. In December 2006, the C-130 became the fourth aircraft – after the English Electric Canberra in May 2001, the B-52 Stratofortress in January 2005 and the Tupolev Tu-95 in January 2006 – to mark 50 years of continuous use with its original primary customer, in this case the United States Air Force. The C-130 remains in production as the updated C-130J Super Hercules.
Capable of short takeoffs and landings from unprepared runways, the C-130 was originally designed as a troop, medical evacuation and cargo transport aircraft. The versatile airframe has found uses in a variety of other roles, including as a gunship, and for airborne assault, search and rescue, scientific research support, weather reconnaissance, aerial refuelling and aerial firefighting. The Hercules family has the longest continuous production run of any military aircraft in history. During more than 50 years of service the family has participated in military, civilian and humanitarian aid operations.

Type: STOL military transport
Crew: 4-6
Manufacturer: Lockheed
Models: see variants

Maiden flight: Aug. 23, 1954
Service Delivery: Dec. 1956
Number built: 2,262+ as of 2006

Specifications - C-130H Hercules
Powerplant:
Model: Allison T56-A-15
Type: turboprop
Number: 4
Horsepower: 4,300 shp
Dimensions:
Length: 97 ft 9 in (29.8 m)
Wingspan: 132 ft 7 in (40.4 m)
Height: 38 ft 3 in (11.6 m)
Wing area: 1,745 ft² (162.1 m²)
Weights:
Empty weight: 83,000 lb (38,000 kg)
Useful load: 72,000 lb (33,000 kg)
Max takeoff: 155,000 lb (70,300 kg)

Performance:
Max speed: 379 mph (610 kph)
Cruise speed: 336 mph (540 kph)
Range: 2,360 mi (3,800 km)
Service ceiling: 33,000 ft (10,000 m)

Payload:
45,000 lb (20,000 kg) including
2-3 Humvees or an M113 APC
Capacity:
– 92 passengers or
– 64 airborne troops or
–74 litter patients with 2 medical personnel

Sources:
Wikipedia: C-130 Hercules

C-123 Provider Fairchild

The C-123 Provider was an American military transport aircraft designed by Chase Aircraft and subsequently built by Fairchild Aircraft for the United States Air Force. It went on to serve most notably with various armed forces in South East Asia.
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Design and development
The C-123 Provider was designed originally as an assault glider aircraft for the United States Air Force (USAF) by Chase Aircraft as the XCG-20 (Chase designation MS-8 Avitruc). Two powered variants of the XCG-20 were developed during the early 1950s, as the XC-123 and XC-123A. The only difference between the two was the engine. The XC-123 used two Pratt & Whitney R-2800-CB-15 air-cooled radial piston engines, while the XC-123A used two General Electric J47-GE-11 turbojets, the same as those on the Boeing B-47 Stratojet. It was initially well regarded for tactical troop transport for its ruggedness and reliability and ability to operate from short and unimproved airstrips, which meant the low slung turbojets, prone to ingesting foreign objects, were dropped in favor of the more conventional option. The XC-123A had its engines replaced with R-2800s and was redesignated YC-123D.
By 1953, Henry J. Kaiser purchased a majority share in Chase Aircraft, feeling that after having completed C-119s for Fairchild under contract, he could take control of the impending C-123 contract. Two airframes were completed at Kaiser's Willow Run factory in Ypsilanti, Michigan, before personal politics led to Kaiser's being told that no further contracts would be honored with him. The C-123 contract was put up for bid, and the two completed airframes scrapped. The contract was finally awarded to Fairchild Engine and Airplane, who assumed production of the former Chase C-123B, a refined version of the XC-123.
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Type: Cargo aircraft
Crew: 3
Manufacturer:
– Chase Aircraft
–Fairchild Aircraft

Models: see variants
Maiden flight: Oct. 14, 1949
Service Delivery: N/A
Retired (from U.S. Service): N.A
Number built: N.A
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Specifications: C-123K Provider
Powerplant:
Model: General Electric J85-GE-17
Type: Turbojet
Number: Two
Thrust: 2,850 lb. each
Model: Pratt & Whitney R-2800-99W
Type: 18-cylinder radial "Double Wasp"
Number: Two
Horsepower: 2,300 lb. each
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Dimensions:
Length: 76.25 ft (23.92 m)
Wingspan: 110 ft (33.53 m)
Height: 34 ft (10.36 m)
Wing area: 1,223 ft² (113.6 m²)

Weights:
Empty: 35,366 lb (16,042 kg)
Loaded: 60,000 lb (27,000 kg)
Max takeoff: N/A
Performance:
Maximum speed: 228 mph (367 kph)
Combat Radius: N/A
Range: 1,035 mi (1,666 km)
Service ceiling: 29,000 ft (8,800 m)
Rate of climb:
– 1,150 ft/min (5.8 m/s) without jets
Wing loading: 49 lb/ft² (240 kg/m²)
Power/mass (prop):
– 0.077 hp/lb (130 W/kg)
Thrust/weight (jet): 0.10
Capacity: 62 passengers
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Sources:
Wikipedia: C-123 Provider