JF-17 THUNDER/ FC-1

1. Aerodynamic Configuration

Bifurcated side air inlet.
New wing with ability of high angle of attack
Leading edge maneuvering flap
Trailing edge flap
Tip missiles
Twin Ventral Fin
Aerodynamic Changes in PT-4

2. New Landing Gear

Nose gear with steering
Main gear with paddle controlled hydraulic brakes and automatic anti-skid braking system
3. Comfortable Cockpit and Safe Escape System

Cockpit geometry conforming to US MIL Standard, suitable for 3% to 98% pilot anthropometrics
Single Piece stretch acrylic transparent canopy providing a good all around Field of View
Ejection Seat
Martin Baker high performance ejection seat
Canopy severance system for additional safety
French oxygen regulation system
4. New Environment Control System, providing:

Air supply to control cockpit pressure and temperature
Air supply for cooling Avionics
Air supply to pilot pressure suit
Air supply for windscreen defogging
Oxygen supply duration three hours
5. New Designed Flight Control System

JF-17 has composite flight control system comprising conventional controls with stability augmentation in roll and yaw axis and fly by wire in pitch axis.
Simple autopilot
Control system of lift increasing device, leading edge slats / flap and trailing edge flaps will be an automatic control system referring to air speed and angle of attack for improving aircraft maneuvering
6. New Electrical Power Supply System

Main power supply system will be 115V, 400Hz three phase AC and 27V DC combined system.
Essential power will be provided by a hydraulic driven AC / DC combined generator in case of Main System Failure
Emergency power will be provided by a set of batteries, in the event of engine flameout, for engine restarting, communication and navigation
7. Fuel System

Total internal fuel 5130 lb
Single point pressure refuelling system
External Fuel
One center line drop tank 800 liters
Two under wing drop tanks 800/1100 liters
8. Strength and Fatigue Life

JF-17 airframe is made of semi-monologue structure
High strength steel and Titanium alloy adopted partially at some critical places.
Max speed: 1350 KPH (Mach 1.8)
JF-17 aircraft would be designed, tested and proofed against the requirement tailored for MIL-A-8860 and Chinese National Military Specification GJB67-85
The desired fatigue life of the JF-17 airframe is 4,000 flight hours or 25 years
The period to first overhaul would be 1,200 flight hours