By 1964, the Chengdu J-7 was inadequate to perform long-range, high-altitude interceptions. The Chinese Aeronautical Establishment held a conference on 25 October to discuss future fighters. The 601 Institute had two proposals; a twin-engined "scaled-up" J-7 which became the J-8,[4] and a higher-performing single-engined option that became the J-9. The J-9 was technically riskier; it was not based on an existing design, and the required engine - an afterburning turbofan generating 83 kN (19,000 lbf) dry and 121 kN (27,000 lbf) reheat thrust - did not exist in China.[1] Shenyang developed a delta and a double-delta concept in 1965.[2]
Development was officially approved following a Ministry of Aerospace Industry (MAI) conference on 12-17 January 1966[1] with the goal of either an air superiority fighter or a pure interceptor. This was revised on April 1 with new requirements for endurance, rate of climb, and significantly increased range. A development schedule was approved on April 12.[2] Shenyang responded first with the J-9A-IV (a tailed delta with lateral intakes) and then the J-9B-V (a tailless-delta); the former was unable to meet requirements. The Cultural Revolution paused development.[2] Development on the J-9B-V resumed in 1968. The goal of flying a prototype by the 20th anniversary of the PRC in October 1969 could not be achieved due to major development problems. MAI shifted work back to the J-9A-IV. In addition, development was transferred to Chengdu because Shenyang was now fully occupied with the J-8. Wang Shounan became the new chief designer.[2]
The Ministry of Defense issued new requirements on 9 June 1970 - and slightly revised in November - for even greater range, speed, and altitude. Chengdu abandoned the J-9A-IV, and reworked the J-9B-V into the J-9B-VI. The J-9B-VI was a canard-delta with lateral intakes; a single ventral intake was rejected. The intended engine, the Woshan WS-6 turbofan, encountered development problems; a reverse-engineered Khachaturov R29-300 turbojet, to be called the WS-15, was selected as a less powerful alternative.[2]
The requirements were revised in February 1975, calling for more range and an armament of four PL-4air-to-air missiles. In November the State Planning Commission approved funding for five prototypes, with the first flight to take place in late-1980 or early-1981. However, the program was ended in 1980.[2]
Gordon, Yefim; Komissarov, Dmitry (2008). Chinese Aircraft: China's aviation industry since 1951. Manchester: Hikoki Publications. ISBN978-1-902109-04-6.
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January 06, 2023
chengdu, this, article, about, fighter, trainer, guizhou, chinese, interceptor, aircraft, that, cancelled, during, development, people, republic, china, proposed, 1964, institute, shenyang, higher, performing, alternative, shenyang, development, disrupted, cul. This article is about the jet fighter For the J L 9 jet trainer see Guizhou JL 9 The Chengdu J 9 Chinese 歼 9 was an interceptor aircraft that was cancelled during development in the People s Republic of China PRC It was proposed in 1964 by the 601 Institute Shenyang as a higher performing alternative to the Shenyang J 8 1 Development was disrupted by the Cultural Revolution and frequently changing requirements in addition development was transferred to the 611 Institute Chengdu The program was cancelled in 1980 2 3 J 9Role InterceptorManufacturer Chengdu Aircraft Industry CorporationDesigner Chengdu Aircraft Design InstituteStatus Cancelled in 1980 Contents 1 Development 2 Specifications J 9B VI 3 See also 4 References 4 1 Citations 4 2 Bibliography 5 External linksDevelopment EditBy 1964 the Chengdu J 7 was inadequate to perform long range high altitude interceptions The Chinese Aeronautical Establishment held a conference on 25 October to discuss future fighters The 601 Institute had two proposals a twin engined scaled up J 7 which became the J 8 4 and a higher performing single engined option that became the J 9 The J 9 was technically riskier it was not based on an existing design and the required engine an afterburning turbofan generating 83 kN 19 000 lbf dry and 121 kN 27 000 lbf reheat thrust did not exist in China 1 Shenyang developed a delta and a double delta concept in 1965 2 Development was officially approved following a Ministry of Aerospace Industry MAI conference on 12 17 January 1966 1 with the goal of either an air superiority fighter or a pure interceptor This was revised on April 1 with new requirements for endurance rate of climb and significantly increased range A development schedule was approved on April 12 2 Shenyang responded first with the J 9A IV a tailed delta with lateral intakes and then the J 9B V a tailless delta the former was unable to meet requirements The Cultural Revolution paused development 2 Development on the J 9B V resumed in 1968 The goal of flying a prototype by the 20th anniversary of the PRC in October 1969 could not be achieved due to major development problems MAI shifted work back to the J 9A IV In addition development was transferred to Chengdu because Shenyang was now fully occupied with the J 8 Wang Shounan became the new chief designer 2 The Ministry of Defense issued new requirements on 9 June 1970 and slightly revised in November for even greater range speed and altitude Chengdu abandoned the J 9A IV and reworked the J 9B V into the J 9B VI The J 9B VI was a canard delta with lateral intakes a single ventral intake was rejected The intended engine the Woshan WS 6 turbofan encountered development problems a reverse engineered Khachaturov R29 300 turbojet to be called the WS 15 was selected as a less powerful alternative 2 The requirements were revised in February 1975 calling for more range and an armament of four PL 4 air to air missiles In November the State Planning Commission approved funding for five prototypes with the first flight to take place in late 1980 or early 1981 However the program was ended in 1980 2 Specifications J 9B VI EditData from 2 3 General characteristicsWing area 55 7 m2 600 sq ft including canards Empty weight 13 000 kg 28 660 lb Powerplant 1 Woshan WS 6 turbofan engine 122 5 kN 27 500 lbf thrust or WS 15 reverse engineered Khachaturov R29 300 turbojet 81 kN 18 000 lbf thrustPerformance Maximum speed Mach 2 5 at 23 000 m 75 000 ft Range 2 000 km 1 200 mi 1 100 nmi Rate of climb 220 m s 43 000 ft min Armament Missiles 4 PL 4 air to air missilesAvionics Type 205 radarSee also Edit China portal Aviation portalChengdu J 10Aircraft of comparable role configuration and era Saab 37 Viggen Mikoyan Gurevich Ye 8Related lists List of fighter aircraftReferences EditCitations Edit a b c Gordon and Komissarov 2008 page 90 a b c d e f g h Gordon and Komissarov 2008 page 91 a b Gordon and Komissarov 2008 page 92 Gordon and Komissarov 2008 page 75 Bibliography Edit Gordon Yefim Komissarov Dmitry 2008 Chinese Aircraft China s aviation industry since 1951 Manchester Hikoki Publications ISBN 978 1 902109 04 6 External links Edit Wikimedia Commons has media related to Chengdu J 9 Interview J 9 Chief Designer Wang Nanshou Chinese language Retrieved from https en wikipedia org w index php title Chengdu J 9 amp oldid 1101315873, wikipedia, wiki, book, books, library,
