Based on Kawasaki’s KA-850 project, the T-4 was selected as the JASDF’s new advanced trainer in 1981 to replace the T-33 and Mitsubishi T-1. Kawasaki is the prime contractor, with Fuji and Mitsubishi each taking a 30 per cent share of the pro¬gramme. The aircraft is a mid-wing, twin-turbofan design which uses two indigenous IHI XF3-30 engines and is equipped with Stencel ejection seats, a headup display, an air data computer, and five hardpoints for auxiliary fuel and light weapons. Future developments may include a dedicated ground¬attack version. Construction of 32 T.4 advanced trainers has been authorised to 1987, against an even¬tual JASDF requirement for more than 200 aircraft, and production of the first batch of 12 was under way, with initial deliveries due in 1988. Four XT-4 prototypes, the first of which flew on July 29, 1985, were engaged in an intensive test programme which was to be completed by March 1988.
The defence Agency awarded the T-4 a type certificate in July 1988.
XT-4 Engine: 2 x IHI XF3-30 turbofan. Installed thrust: 32.6 kN. Span: 10 m. Length: 13 m. Wing area: 21.6 sq.m Empty wt: 3700 kg. MTOW: 7500 kg. Max speed: M0.9. Initial ROC: 3000 m / min. Ceiling: 15,240 m. T/O run: 549 m. Ldg run: 670 m. Fuel internal: 2271 lt. Range: 1300 km. Hardpoints: 5.
Developed to replace OH-6Ds of JGSDF, the Japan Defence Agency (IDA) awarded Y2.7 billion (US$22.5 million) in FY92 to cover the basic design phase of the helicopter then provisionally designated OH-X. Requests for proposals were issued by JDA’s Technical Research & Development Institute (TRDI) 17 April 1992 and Kawasaki was selected as the prime contractor (60% of programme) on 18 September 1992, with Fuji and Mitsubishi (20% each) as partners. The Observation Helicopter Engineering Team (OHCET) was formed by these three companies, beginning with a preliminary design phase 1 October 1992. A mockup was made public on 2 September 1994 under the Japanese name Kogata Kansoku (new small observation [helicopter]). The programme included six prototypes (four flying, two for ground test), and the first aircraft (32001) rolled out at Gifu on 15 March 1996 and made first flight 6 August 1996, followed by second prototype on 12 November. The OH-1 designation was assigned late 1996. The first two XOH-ls were handed over to JDA on 26 May and 6 June 1997. The third flown on 9 January 1997, at which time the earlier aircraft had accumulated some 30 and 20 hours, respectively. The third was handed over on 24 June 1997. The fourth was flown on 12 February 1997 and handed over 29 August 1997. The prototypes were renumbered by 1999 from 32001-04 to 32601-04. The Japan Defence Agency’s Technical Research and Development Institute was looking to develop an attack version of the Kawasaki OH 1 armed reconnaissance helicopter which in 1998 was at the flying prototype stage. Consideration was being given to replacing the OH 1’s single Mitsubishi XTS1 10 engine with two LHTEC T800 or MTU/Turbomeca&Rolls-Royce MTR 390 turboshafts for the AH 2, together with a new gearbox and rotor system, plus a new integrated sensor targeting and weapon system. The first three production OH-1s were funded FY97 and ordered in 1998. The first prototype was flown with more fuel-efficient TS1-10QT (replacing XTS1-10) engines, on 30 March 1998. By early 1999, four prototypes had flown 450 hours and were due to complete further 450 hours by end of 1999, including operational evaluation at Akeno JGSDF base. The first production OH-1 (32605) flown July 1999 and handed over to JGSDF at Gifu 24 January 2000. Name ‘Ninja’ reportedly given in 2002, but not officially confirmed.
The OH-1 features Kawasaki hingeless, bearingless and 20mm ballistic-tolerant four-blade elastomeric main rotor and transmission system; Fenestron-type tail rotor with eight unevenly angled ‘scissor’ blades (35 and 55 degrees); stub-wings for stores carriage. Active vibration damping system. Flying controls are integrated AFCS and stability control augmentation system (SCAS). The rotor blades and hub are manufactured from GFRP composites; centre-fuselage and engines by Mitsubishi, tail unit/canopy/stub-wings/cowling by Fuji, rest by Kawasaki. Some 37% of airframe (by weight) in GFRP/CFRP. The landing gear is a non-retractable tailwheel type, with provision for wheel/skis on the main units. Power is from twin 662kW FADEC-equipped Mitsubishi TS1-10QT turboshafts (XTS1-10 originally in prototypes), and the transmission has a 30-rninute run-dry capability. Stub-wings can each carry a 235 litre auxiliary fuel tank. The crew of two are on tandem armoured seats (pilot in front) with flat-plate cockpit transparencies, upward-opening on the starboard side for crew access. Armament is four Toshiba Type 91 (modified) lightweight short-range, IR-guided AAMs on pylons under stub-wings for self-defence.
Funding for development, prototypes and flight testing Y2.5 billion in FY92, Y10.2 billion in FY93, Y50.1 billion in bY94 and Y23.3 billion in FY95. Unit costs of first four production lots Y1.924 billion (FY97), Y2.018 billion (FY9S), Y2.229 billion (FY99) and Y2.075 billion (FY00).
The Hiko Jikkentai (Flight Test Squadron) was formed at Akeno with first four production aircraft on 27 March 2001; other deliveries by late 2002 included small numbers to Kasumigaura Bunko, Utsunomiya Bunko and Kyoiku Shien Hikotai (at Akeno), all of which are departments of the Army’s Koku Gako (Aviation School). A total of 20, including prototypes, were ordered by FY02, and at least 12 delivered by late 2002.
OH-1 Engines: 2 x Mitsubishi TS1-10 Main rotor diameter: 11.6m Fuselage length: 12.0m Height to top of rotor head: 3.4m Height over tailfin: 3.8m Empty weight: 2450kg Normal take-off weight: 3550kg Max take-off weight: 4000kg Max level speed: 277km/h Combat radius: 200km Range: 550km
Designed to replace the JASDF’s Curtiss C 46 Commando transport aircraft, the Kawasaki C 1 first flew on 12 November 1970 and was delivered from December 1974.
Power is provided by two 14,500 lb thrust Mitsubishi produced Pratt & Whitney JT8 M 9 turbofan engines and it can carry 60 troops, 45 paratroops, 36 stretchers, or 26,235 lb (11,900 kg) of freight (including vehicles).
Inordinately expensive because of Japan’s relative inexperience in creating this type of airplane, by law the C 1 could not be sold abroad. Production ceased after 31 were built for the Japanese military, by a consortium of companies including Mitsubishi Heavy Industries, Kawasaki Heavy Indus¬tries, Fuji Heavy Industries, Nihon, Shin Meiwa and Sumitomo Precision practically all the companies involved in Japanese aircraft production.
By 1981 the 31 production C-1s had been delivered, including several long-range aircraft with an additional 4,732 litre wing centre-section fuel tank.
Kawasaki has modified a single C-lA twin-jet tactical transport for use in the ECM training role. Serialled 78 1021, the aircraft was fitted with seven radomes. Featuring nose and tail radomes housing elements of the TRDI/Mitsubishi Electrics XJ/ALQ-5 ECM system, the C-1ECM completed trials with the JASDF’s Air Proving Wing in 1986, and is now in service with the Electronic Warfare Training Unit.
Variation: Science & Technology Agency Asuka
C-1 Engines: 2 x P+W JT80D-M-9A, 64.5kN Wingspan: 30.6 m / 100 ft 5 in Length: 29.0 m / 95 ft 2 in Height: 10.0 m / 32 ft 10 in Wing area: 120.5 sq.m / 1297.05 sq ft Max take-off weight: 38600 kg / 85099 lb Empty weight: 23700 kg / 52250 lb Max. speed: 815 km/h / 506 mph Cruise speed: 705 km/h / 438 mph Ceiling: 12200 m / 40050 ft Range w/max.fuel: 3300 km / 2051 miles Range w/max.payload: 1300 km / 808 miles Crew: 5 Passengers: 60
At the beginning of the sixties, Kawasaki began to develop a version of the three-seat Bell Model 47G-3B, with a stretched cabin to make room for two rows of seats. Powered by a 201kW Lycoming TVO-435-B1A air-cooled engine, the first KH-4 flew in August 1962 and received Japanese type approval on 9 November of that year. Apart from changes to the cabin to accommodate extra passenger, and new supercharged engine, the KH-4 had a new instrument layout, modified control system and larger fuel capacity. The engine retained was a 270hp Lycoming TVO-435-B1A or -D1A. By the beginning of 1972, 193 of the Kawasaki KH-4 had been built, 19 of which were assigned to the Japanese Army, 23 to the Thai armed forces, four to the South Korean armed forces and one to the Philippines. A total of 338 built for civil and military customers between 1960 and 1975. An experimental variant of the KH-4 was the KHR-1 which was modified to test a three-blade rigid rotor system. This aircraft flew for the first time on 26 April, 1968.
KH-4 Rotor diameter: 11.32m Length overall: 13.30m Length of fuselage: 9.93m Height overall: 2.84m Empty weight: 816kg Maximum take-off weight weight: 1293kg Maximum level speed: 169km/h Cruising speed: 140km/h Service ceiling: 5640m Hover ceiling in ground effect: 5485m Maximum range: 400km
The Kawasaki KAL-1 was the first post-war all-metal aircraft of Japanese design. Flown for the first time on 21 July 1953, the KAL-1 was built by the Kawasaki Gifu works and powered by a 260 hp Lycoming GO-435-C-2 engine. Two prototypes were completed.
Designed as a four-seat liaison aircraft for the Japanese Air Self-Defence Force, the KAT-1 tandem two-seat basic trainer employs a similar wing and tail assembly.
Engine: 260 hp Lycoming GO-435-C-2 Wing span: 34 ft 1.5 in Wing area: 196 sq.ft Length: 29 ft 6 in Height: 8 ft 2.5 in Empty weight: 2022 lb Loaded weight: 3230 lb Max speed: 174 mph Cruise speed: 167.5 mph Service ceiling: 19,700 ft Max range: 1000 mi
The Kawasaki Ki-108 pressurised high-altitude fighter was developed from the Ki-102 in 1943. Four were completed; two modified from Ki.102b.
Ki-108 KAI Engines: 2 x Mitsubishi Ha-112-II Ru, 1125kW Wingspan: 15.67 m / 51 ft 5 in Length: 11.71 m / 38 ft 5 in Height: 3.7 m / 12 ft 2 in Wing area: 34 sq.m / 365.97 sq ft Max take-off weight: 7200 kg / 15873 lb Empty weight: 5300 kg / 11685 lb Max. speed: 580 km/h / 360 mph Ceiling: 13500 m / 44300 ft Range: 1800 km / 1118 miles Armament: 1 x 37mm cannon, 2 x 20mm cannons Crew: 1
Derived from the Ki-96 twin-engine single-seat fighter, the Kawasaki Ki-102b was intended as a two-seat attack fighter. Some assemblies of the Ki-96 prototypes were incorporated into the three Ki-102 prototypes, the first completed in March 1944.
A cantilever mid-wing monoplane with a conventional tail unit, retractable tailwheel landing gear and two Mitsubishi Ha-112-11 radial engines, the Ki-102 carried a two-man crew in separate enclosed cockpits in tandem.
The prototypes were followed by the construction of 20 pre-production aircraft and in October 1944 the type was ordered into production.
Kawasaki modified six of the preproduction Ki-102s to serve as prototypes of a twin-engine high-altitude fighter for the Imperial Japanese Army. This differed from the attack fighter by having improved two-seat accommodation, a revised tail unit and Mitsubishi Ha-112-IIru engines with turbochargers. Successful testing of this version in mid-1944 resulted in a high-priority production order, but problems with the turbocharged engine resulted in only about 15 being delivered to the army before the war ended.
The design had also been revised to produce a night-fighter version under the designation Ki-102c, but only two examples were completed. These had increased wing span, a lengthened fuselage, redesigned tail surfaces, primitive AI radar, and armament of two 30mm Ho-105 cannon in the underfuselage and two 20mm Ho-5 cannon mounted obliquely in the fuselage to fire forward and upward.
Twenty Ki.102b were built with one 57mm and two 20mm cannon, one 12.7mm machine gun and provision for 1100 lb of bombs. Maximum range was 1243 miles and ceiling just over 36,000 ft.
Ki-102b aircraft, which were allocated the Allied codename ‘Randy’, saw comparatively little service, some being used in action over Okinawa, but the majority were held in reserve in Japan.
Ki-102b Engines: 2 x Mitsubishi Ha-112-II, 1125kW Wingspan: 15.57 m / 51 ft 1 in Length: 11.45 m / 37 ft 7 in Height: 3.7 m / 12 ft 2 in Wing area: 34 sq.m / 365.97 sq ft Max take-off weight: 7300 kg / 16094 lb Empty weight: 4950 kg / 10913 lb Max. speed: 580 km/h / 360 mph Ceiling: 13500 m / 44300 ft Range: 2000 km / 1243 miles Armament: 1 x 57mm cannon, 1 x 12.7mm machine-guns Crew: 2
The Japanese Army was faced with the prospect of having 270 Ki-61-II airframes sitting around waiting for installation of their Ha-140 liquid-cooled engines.
The Ha-140 engine had proven to be totally unreliable, and, to make matters worse, the Akashi factory manufacturing the Ha-140 had been destroyed in a B-29 raid. Since Japan desperately needed aircraft capable of intercepting the B-29, in November of 1944 the Ministry of Munitions instructed Kawasaki to install a different powerplant in the 275 Ki-61-II airframes gathering dust in the Kagamigahara factory in an attempt to get as many aircraft in the air as possible.
Kawasaki settled on the 1500 hp Mitsubishi Ha-112-II fourteen-cylinder double-row radial engine. This engine had established a standard of easy maintenance and reliable service, however, the Ha-112 was a radial engine, and, with a diameter of four feet, the installation of this engine in a fuselage only 33 inches wide provided a major challenge. The Kawasaki concern was guided in its work by being able to study the engine mount in an imported Focke-Wulf Fw 190A, an example in which a wide radial engine had been successfully installed in an airframe with a narrow width. In addition, the same Mitsubishi Ha-112 radial engine had been successfully installed in the Aichi-built D4Y3 (Allied code name JUDY) dive bomber, earlier versions of which had been powered by a liquid-cooled engine.
Kawasaki’s design team converted three airframes to serve as prototypes, installing a Mitsubishi Ha-112-II engine which had the same power output as the unreliable Ha-140. The new project was sufficiently different from the Ki-61 Hien that it was assigned a new Kitai number: Ki-100.
The first Ki-100 prototype aircraft made its first flight on February 1, 1945. The results of the flight testing exceeded everyone’s expectations. The Ki-100 was about 600 pounds lighter than its Ki-61-II predecessor. Maneuverability and handling were markedly improved due to the lower wing and power loading.
Although the maximum speed of the Ki-100 was slightly lower than that of the Ki-61-II because of the higher drag exerted by the radial engine, this performance could be reliably attained because of the better reliability of the Ha-112 engine. The design was ordered into immediate production as the Army Type 5 Fighter Model 1A (Ki-100-Ia). The first Type 5 fighters (Ki-100-Ia) were direct conversions of existing Ki-61-II airframes. 271 airframes were converted between March and May 1945, and were immediately delivered to operational units.
The Ki.100 also had provision for carrying two 550 lb bombs externally.
In combat, the Ki-100-Ia proved to be an excellent fighter, especially at low altitudes. It possessed a definite ascendancy over the Grumman F6F Hellcat. In one encounter over Okinawa, a Ki-100-equipped unit destroyed 14 F6F Hellcat fighters without loss to themselves. When the Ki-100 encountered the P-51D Mustang at low or medium altitudes over Japan, it was able to meet the American fighter on more or less equal terms. The outcome of P-51D vs Ki-100 battles was usually determined by piloting skill or by numerical advantage rather than by the relative merits of the two fighter types. However, at altitudes above 26,000 feet, the maneuverability of the Ki-100 began to fall off rather severely and the fighter was at a relative disadvantage in intercepting the high-flying B-29. With the Ki-100 proving such a success, it was decided to initiate production of this aircraft, the resulting Ki-100-Ib differing only by having the cutdown rear fuselage and all-round-view canopy that had been designed for the proposed Ki-61-III.
The first Ki-100-Ib fighters were built at the Kagamigahara and Ichinomiya Kawasaki factories in May of 1945, but production was severely hampered by the continual Allied bombing. Plans had been made to produce 200 fighters per month, but the Ichinomiya plant was forced to shut down in July 1945 after having built only 12 aircraft, and the Kagamigahara plant had its production severely curtailed by aerial attacks. By the time of the Japanese surrender, only 118 Ki-100-Ib aircraft had been delivered.
Ki.100-1b
In an attempt to improve the high-altitude performance, the Ki-100-II version was evolved. It was powered by a 1500 hp Mitsubishi Ha-112-II Ru with a turbosupercharger and water-methanol injection to boost power for short intervals. Because of a lack of space, the turbosupercharger had to be mounted underneath the engine without provision for an intercooler and its associated ducting, with air being ducted directly from the compressor to the carburetor. It first flew in May 1945. The lack of an intercooler limited the high-altitude performance of the Ki-100-II, and the turbosupercharger added 600 pounds to the weight, which reduced maximum speed by 15 mph at 10,000 feet. However, the boosted high-altitude power enabled a maximum speed of 367 mph to be be reached at 32,800 feet (the cruising altitude of the B-29 during daylight operations). It had been planned to begin production of the Ki-100-II in September of 1945, but only three prototypes of this high-altitude interceptor had been produced by the time of the Japanese surrender.
A total of 396 Ki-100s were built, including 275 Ki-61-II conversions, 118 Ki-100-Ib production aircraft built from scratch, and three Ki-100-II prototypes. Most of them were assigned to the defense of the home islands, operating from Chofu and Yokkaichi from the spring of 1945. At the end of the war, two Ki-100-Ibs were shipped to the USA for evaluation. The Ki-100 never had a separate Allied code name assigned to it.
Ki-100-I Engine: 1 x Mitsubishi Ha-112-II, 1125kW Max take-off weight: 3495 kg / 7705 lb Empty weight: 2525 kg / 5567 lb Wingspan: 12 m / 39 ft 4 in Length: 8.82 m / 28 ft 11 in Height: 3.75 m / 12 ft 4 in Wing area: 20 sq.m / 215.28 sq ft Max. speed: 580 km/h / 360 mph Cruise speed: 400 km/h / 249 mph Ceiling: 11000 m / 36100 ft Range w/max.fuel: 2200 km / 1367 miles Range w/max.payload: 1400 km / 870 miles Armament: 2 x 20mm cannons, 2 x 12.7mm machine-guns Crew: 1
Kawasaki Ki-100-Ia Army Type 5 Fighter Model 1a Engine: 1 x Mitsubishi [Ha-33] 62 or Ha-112-II, 1500 hp Takeoff, 1350 hp at 6560 ft, 1250 hp at 19,030 ft Wingspan: 34 ft 4 7/16 in Length: 28 feet 11 1/4 in Height: 12 feet 3 5/8 in Wing area: 215.3 sq.ft Empty weight: 5567 lb Loaded weight: 7705 pounds. Max speed: 360 mph at 19,685 ft / 332 mph at 32,810 ft. Time to 16,405 ft: 6 min. Service ceiling: 36,090 ft. Maximum range: 1367 miles. Armament: Two fuselage-mounted 20-mm Ho 5 cannon and two wing- mounted 12.7 mm machine guns.
Ki 100 1b Engine: 1,500 hp Mitsubishi Ha.112 11. Wing span: 39 ft 4.25 in (12m). Length: 28 ft 11.25 in (8.82 m). Height: 12 ft 3.75 in (3.75 m). Wing area, 215.278 sq.ft (20 sq.m). Empty wt: 5,567 lb (2 525 kg). Loaded wt: 7,705 lb (3 495 kg). Max speeds of 317 mph (510 kph) at 3,280 ft (1 000 m), 352 mph (567 kph) at 16,400 ft (5 000 m), 360 mph (580 kph) at 19,685 ft (6 000 m), and 332 mph (535 kph) at 32,800 ft (10000 m). Climb to 16,400 ft (5 000 m): in 6 min, 26,250 ft (8 000 m): 11.5 min, 32,800 ft (10 000 m): 20 min. Service ceiling: 36,090 ft (11000 m). Cruising speed: 248 mph (400 kph) at 13,123 ft (4 000 m). Armament: two 20 mm Ho.5 cannon and two 12.7¬mm Type 103 machine guns.
The first Kawasaki Ki 96 fighter prototype flew in 1943. 3 built.
Ki-96 Engines: 2 x Mitsubishi Ha-112-II, 1125kW Wingspan: 15.57 m / 51 ft 1 in Length: 11.45 m / 37 ft 7 in Height: 3.7 m / 12 ft 2 in Wing area: 34 sq.m / 365.97 sq ft Max take-off weight: 6000 kg / 13228 lb Empty weight: 4550 kg / 10031 lb Max. speed: 600 km/h / 373 mph Ceiling: 11500 m / 37750 ft Range: 1600 km / 994 miles Armament: 1 x 37mm cannon, 2 x 20mm cannons Crew: 1
Ki-78 Engine: 1 x Deimler-Benz DB-601A, 880kW Wingspan: 8 m / 26 ft 3 in Length: 8.1 m / 26 ft 7 in Height: 3.07 m / 10 ft 1 in Wing area: 11 sq.m / 118.40 sq ft Max take-off weight: 2300 kg / 5071 lb Empty weight: 1930 kg / 4255 lb Max. speed: 700 km/h / 435 mph Ceiling: 8000 m / 26250 ft Range: 600 km / 373 miles Crew: 1
