FC-1 "Dragon" fighter adopts medium aspect ratio side strip wing normal aerodynamic layout, the fuselage adopts supersonic area law, beam and semi-monocoque hybrid structure. It has a single vertical tail, differential horizontal tail, twin ventral fins, full wingspan leading edge flaps and trailing edge flaps. The wing, horizontal tail, vertical tail leading edge swept angle is 42 degrees, the large swept edge bar extends to the fuselage tail, and the front three-point landing gear. The cockpit is equipped with a rounded windshield, a blister-shaped canopy, a micro-explosive rope cover, and a "zero-zero" ejection system, which provides a better field of vision and a more reliable ejection system.
The location of the FC-1's two side-ribbed air intakes is designed to improve maneuverability when flying at large head-on angles. The air intakes are located in the lower part of the forward fuselage and are tilted slightly outward to deliver sufficient air to the engine even when flying at large head-on angles. Due to the adoption of the DSI air intake, compression and separation of the attached surface layer, drag reduction, reduce radar reflection wave, no auxiliary intake valve bleeder valve, structure weight greatly reduced, high reliability. Batch production FC-1 use this intake. the aerodynamic shape of the FC-1 fighter aircraft fully in line with the latest trends, with particular emphasis on improving maneuverability.
FC-1 "Dragon" fighter design, to avoid technical risk also used some advanced aerodynamic technology, not only effectively improve the overall combat performance, but also take into account the reliability, with low-cost features.
The structure of the FC-1 is mainly made of traditional materials and technologies and does not make extensive use of composite materials. The use of composite materials is limited to a small number of intakes, nacelles and other parts of the main still use traditional high-strength aviation aluminum. FC-1 design emphasizes low-altitude subsonic maneuverability, sacrificing some high-altitude high-speed performance, with the ability to over-the-horizon air combat. the FC-1 fighter shape is significantly larger than the J-7M, the aircraft's comprehensive combat capability than the J-7 fighter has been substantially improved. The FC-1's engine is a Russian Klimov RD-93 turbofan engine (an improved version of the RD-33 engine used in the MiG-29). The engine has a maximum thrust of 49.4 kN and an additive force of 81.4 kN. In December 2003, AVIC announced that the Guizhou Institute of Aero-Engine Research (GIAER) would cooperate in the development of the FC-1 by developing a new turbofan engine, the WS-13 (a copycat and improved version of the RD-93). The engine has a thrust-to-weight ratio of 7.8 and an accelerated thrust of 86.37 kN. After 2003, France and China discussed the possibility of participating in the FC-1 program by supplying an engine (reportedly Snecma's M88 series engine), but the cooperation was finally put on hold due to the unsuitable political environment at the time.
The FC-1 fighter has an internal fuel capacity of about 3,500 to 3,800 liters of fuel and can carry three external secondary fuel tanks. The aircraft is not fitted with any aerial refueling equipment, but aerial refueling has been factored into the design. The FC-1 is designed with a new generation quad-redundant longitudinal teletype maneuvering system. The aircraft's flight control system is a hybrid system, using both conventional hydraulic transmission and teletype. The dual redundancy longitudinal line-transfer maneuvering system is combined with conventional mechanical controls. This design allows maneuverability, pilot effort and cost to be balanced against each other. Stability and control are enhanced while avoiding the technical risks and high costs associated with the sole application of an electrical transmission system. It is expected that the fly-by-wire system will be fully utilized in the flight control system of the successor to the FC-1.
FC-1's avionics system adopts a centralized and distributed structure, and the basic structure is linked by the 1553B data bus. In order to meet the aircraft's operational and mission requirements, its advanced and integrated avionics and weapons system must have autonomous navigation, air-to-air, ground-to-sea attack, target search and identification, communication and approach and landing, externally mounted object management, mission planning and parameter recording, integrated electronic warfare, integrated display and control, integrated display and control, and integrated electronic warfare, integrated display and control, and integrated display and control. Electronic warfare, integrated display and control, data transmission and other functions; can help the pilot to perform various tactical operations smoothly, provide the aircraft with good characteristics and convenient maintenance capabilities; can mount a variety of weapons, including precision-guided weapons, with the ability to launch medium-range air-to-air missiles to achieve over-the-horizon attack. In addition, according to the different requirements of the user, different avionics system combination programs can be selected. The whole avionics system is divided into several sub-systems such as weapon and mission management, radar, inertial guidance, electronic warfare, communication, navigation and identification, electromechanical management, external object management, atmospheric data and flight control. The main equipments are mission computer; pulse Doppler radar with the functions of medium-range airborne interception, close air combat, ground attack, sea attack, auxiliary navigation, etc. as well as the capability of downward looking and downward shooting in upward looking and ground clutter environment; laser gyro inertial navigation system plus global positioning system; hang-on management system; enemy and self identifier; radar warning receiver; foil/tracer bullet dispenser and data transmission unit, etc. The maneuvering interface is flat, three-down, inertial guidance, atmospheric data management and flight control. The control interface is a flat screen, multi-functional liquid crystal display (LCD), and a two-handed joystick control system. The aircraft may be retrofitted with a Chinese-developed forward-looking infrared device, laser irradiation pods and night-vision goggles. The FC-1 is equipped with a 23-3 twin-barrel 23mm cannon with 220 rounds of ammunition. The aircraft has seven external mounting points, two at the wingtips, four under the wings and one in the center of the belly. The main air combat weapons include Chinese-made active radar-guided SD-10 over-the-horizon missiles and PL-9 infrared-guided close-range combat missiles. Official reports also mention anti-ship and anti-radar missiles, conventional and guided bombs, as well as anti-runway bombs and submunitions, etc. The FC-1's total hang-up capacity can reach 3.6 tons.
In addition to the single-seat basic version of the FC-1 fighter, a two-seat trainer/fighter version is planned for the future. In addition, the fuselage design aspect includes the installation of an arresting hook, giving the FC-1 fighter the potential to develop a shipboard version. Inside the FC-1 Dragon's nose is a KJL-7 multimode Pulse Doppler (PD) radar, which can simultaneously display 40 targets in the field of view and launch simultaneous attacks on two of them .
Dual redundant mission computers
Dual redundant 1553 Mux bus architecture
Multimode Pulse Doppler radar capable of tracking multiple targets with priority fire
Ring laser gyro inertial navigation system with GPS
Smart head with preemptive control panel displays. total field of view of the SHUD is 25 degrees
Color video cameras and recorders (SMFCDs)
Hands-on-the-stick joystick
The cockpit has three smart multifunction color displays (MFDs) and a flat display (HUD)
Atmospheric data computer
Radar altimeter
Enemy identification query/transponder
Air combat maneuvering instrumentation ( ACMI)
BVR / communication data link
hVHF / UHF communication system FC-1 fighter aircraft, using a number of key technologies, such as:
1, aerodynamic layout and "clam" intake (DSI intake) design technology
2, avionics Electronic core technology design and system integration technology
3, cost-effective flight control system design technology
4, power supply and distribution system integrated design technology
5, emergency power supply design technology
6, cockpit cover design technology
7, life-saving system design technology
8, fuel system integrated design technology
9, Integral Fuel Tank Design Technology
10, Titanium Alloy Structure Design Technology