China and Grumman (USA) signed a $550 million agreement to modernize 55 J-7 Fighters under the project called "Super-7". However the project was cancelled due to political problems and significant increases in the cost.
As a substitute to Super-7, China started the FC-1 project. In February 1992, CATIC (China Aero Technology Import and Export Corporation) invited the Pakistan to invest in the project in return for huge Transfer of Technology and participation in R&D of the project. Pakistan Accepted. The First Flight was planned in 1996, but it got delayed because Pakistan wished to upgrade the characteristics in response to India's acquisitions of Su-30MKI. The project began to Stagnate. But in 1998, Pakistani PM's visit to China resulted in the continuation of the Programme. In 1999, sanctions on Pakistan led to serious setbacks on the programme. Pakistan hoped to install Western Avionics on the plane, which was now not possible. Year 2001 saw the changes in approach to develop the fighter plane. The development of airframe was de-linked from the development of Avionics. The Comprehensive design was completed in September 2002 while the development of different aircraft systems progressed. The First Aircraft was assembled by May 2003.
A new redesigned prototype emerged in April, 2006, this was in response to flaws that were discovered in earlier flight tests. The main changes included re-designed air intakes, larger leading edge root extensions (LERX), longer ventral fins underneath the rear of the fuselage, a taller vertical stabilizer fin with a rectangular electronic warfare equipment housing at the tip.
Specifications
General
| Crew : | One |
| Maiden Flight : | August, 2003 |
| Type : | Multi-Role |
| Cost : | $15m-$25m |
Dimensions
| Length | 14.9 m | 49 ft |
| Height | 4.77 m | 15.6 ft |
| Wing Area | 24.4 m² | 263 ft² |
Weights
| Empty Weight | 6,411 kg | 14,134 lb |
| Maximum Take-Off Weight | 12,474 kg | 27,500 lb |
| Maximum Landing Weight | 7,802 kg | 17,200 lb |
| Fuel Weight | 2,268 kg | 5000 lb |
Performance
| Maximum Speed | 1,910 km/h – 1,187 m/h | 1.6 Mach |
| Ferry Range | 2,037 km | 1,266 miles |
| Operational Radius | 1,352 km | 850 miles |
| Service Ceiling | 16,794 m | 55,500 ft |
| Thrust/Weight | 0.95 | |
| G-Limit | +8 / -3 | |
| Hardpoints | 7 |
Engine
| Name | Klimov RD-93 | Guizhou WS-13 |
| Type | Turbofan | Turbofan |
| Origin | Russia | China |
| Number of Engines | One | One |
| Dry Thrust | 49.4 kN | 51.2 kN |
| Thrust After Burner | 84.4 kN | 86.37 kN |
Avionics
JF-17 Avionics Architecture will be supported by two mission computers based on around Multi-Bus System (MIL-STD-1553B). The heart of the system is a 32-bit Weapon and Mission management Computer (WMMC) which performs mission computations, flight management, reconfiguration / redundancy management and in-flight system self-test.
The Aircraft will be equipped with advanced multi-track, multi-mode, pulse Doppler radar for air to air, air to surface attack capabilities. Accurate navigation and guidance is realized through hybrid technology using Ring Laser Gyros (RLG) based Inertial Navigation System (INS) and Global Positioning System (GPS). Independent Data link with 2 Independent Wide-Band Radios will take care of communication even during intense EW environment . EW suite comprises of Self Production Jammer (SPJ), Missile Approach Warning System (MAWS), Radar Warning Receiver (RWR), Chaff & Flare Dispenser (CFD). Laser Designator and Targeting Pod (LDTP) is for target illumination and detection with day/ night capabilities.
Glass cockpit uses Smart Multifunction Color Display (SMFCD) and Smart Heads-Up Display (SHUD) with built in symbol generation capability to optimize integrated architecture. ICP and HOTAS arrangement. Identification of Friend and foe (IFF) implements Secure mode for EW environment. Target verification is with onboard IFF interrogator for BVR missile firing.
JF-17 Radar
A Chinese radar KLJ-7 has been selected for the initial batch of JF-17s.
KLJ-7 is a multi–function X-band Pulse-Doppler fire control radar. It was developed by Nanjing Research Institute of Electronic Technology (NRIET), also known as the China Electronics Technology Company's (CETC's) No. 14 Research Institute.
Specifications
- Frequency: X band
- Operation range (RCS of 5 m2) :
Up-looking detection range >105KM
Down-looking detection range >85km - Management of up to 40 targets
- Numbers of simultaneously tracked targets: 10
- Simultaneously fire on 2 BVR targets
- Weight: <120 kg
- Meantime between failure: 220 hours
- Meantime to recovery: 0.5 hours
Features
14 Operational Modes:
JF-17 Cockpit
Engine
Klimov RD-93
JF-17 Thunder currently uses Klimov RD-93, a variant of RD-33 Engine. It has been reported that a Chinese engine Guizhou WS-13 Taishan is under development to replace RD-93 eventually.
RD-93 has been developed by Klimov Design Bureau in St. Petersburg. It is a variant of Klimov RD-33 Turbofan Engine which powers the MIG-29 Fulcrum. The most significant difference being the repositioning of the gearbox along the bottom of the engine casing.
Specifications
Thrust (Afterburner): 8300 kgf /18,260 lb
Specific Fuel Consumption: 2.1 kg/kgf/Hr in afterburner, 0.77 military
Bypass Ratio: 0.46
Compressor Pressure Ratio: 21
Maximum Turbine Inlet Temperature: 1680 K
Service Life, hr: 4000
Length: 4.230m
Maximum Diameter: 1.040m
Mass: 1055 kg
One of the criticisms levelled against RD-93 has been its nature to emit black smoke, which makes it easier for the enemy pilot to spot the plane in close combat. This puts the pilot in inferior position during a dogfight. However, the emission of black smoke is not contineous as observed from JF-17's performance in Zhuahi and Izmir Airshow. The emission is observable for a short amount of time on certain levels of throttle.
The sage of JF-17's engine is not without controversies. The contract between China and Russia over re-exporting the engines to Pakistan had ran into dispute due to Russian fears that JF-17 may compete against Mig-29 in export markets. Recently tho, the supply seems to be smooth without any problems.
Guizhou WS-13
China is also working on an indigenous engine which has the potential to power the FC-1 in future. The engine is known as WS-13 Taishen. It is a turbofan engine developed by Guizhou Aircraft Industry Corporation. It was reported that JF-17 had been tested with the engine in early 2010.
Specifications
Maximum thrust: 51.2 kilonewtons (11,500 lbf) dry; 86.37 kilonewtons (19,420 lbf) with afterburner
Length: 4.14 metres (13.6 ft)
Diameter: 1.02 metres (3 ft 4 in)
Dry weight: 1,135 kilograms (2,500 lb)
Compressor: Two-spool 8-stage axial
Combustors: annular
Bypass ratio: 0.57:1
Turbine inlet temperature: 1650 K (1,377 °C (2,511 °F))
Thrust-to-weight ratio: 7.8
There have been reports of 100kN/22,450lbs thrust version under development.