General (Allgemeine Angaben)
The Design Bureau started work to produce a Su-30-based two-seat attack aircraft designated Su-30MKK for China's Air Forces in 1997, A.I. Knyshev having been appointed chief designer of the project. Under the contract, the Komsomolsk-on-Amur production plant (KnAAPO) was named as the general contractor. The Design Bureau produced a detailed design in 1997-98; the prototype planes were made in Komsomolsk-on-Amur in 1998-99.
The new version of the two-seater was based to a great extent on the design solutions adopted for the Su-27SK and the single-seat fighter Su-27M. As a result, the Su-30MKK incorporated, for all intents and purposes without any redesign, the Su-27M's centre wing section, wing panels, air intakes, tail beams, fins and landing gear and the Su-27SK's tail-end fuselage assemblies. This way, the design scope was reduced dramatically, without any new components required for building the aircraft except for the nose. Besides, the production plant had already gained experience in setting up production of a two-seat trainer at the beginning of the '80s.

Su-30MKK design highlights:

- The plane features upgraded equipment of Russian manufacture, which includes a new version of radar with target designation and mapping capabilities; OSTS with target illumination using a laser beam; a GPS system, and a coloured multi-function LCDs in the cockpit, etc.;
- The ADO line-up has been upgraded with the addition of RVV-AYe air-to-air guided missile; Kh-29L/T/TYe, Kh-31P, Kh-59M air-to-ground missiles; and KAB-500 and KAB-1500 guided bombs. The Su-30MKK has been used as a platform to produce an upgraded version, the Su-30MK2, which differs from the parent version in its weapons and equipment systems configuration; planes of this type were been supplied to China in 2003. In addition, Su-30MK type aeroplanes were supplied to Indonesia in 2003.

Customers (Kunden)
Indonesia, China, Russia.

Remarks (Bemerkungen)
The first prototype was built in the spring of 1999, the Su-30MKK-1 having been taken off the ground for its maiden flight on 20th May 1999 by test pilots I.Ye. Solovyov (Design Bureau) and A.V. Pulenko (KnAAPO). The first four pre-production planes were handed over to the Design Bureau for testing. The testing was conducted jointly with SPFC of the Air Forces in 1999-2001, with the first 10 production Su-30MKK planes delivered to the customer in December 2000.

Aircraft performance
Takeoff weight:
- normal (including rockets 2xR-27R1 + 2xR-73E, 5270 kg fuel), kg	24,900*
- maximum, kg	34,500
- max, kg	38,800
Maximum landing weight, kg	23,600
Max landing weight, kg	30,000
Maximum internal fuel, kg	9,640
Normal internal fuel, kg	5,270
Maximum ordnance, kg	8,000
Service ceiling (without external ordnance and stores), km	17.3
Maximum flight speed at sea level (without external ordnance and stores), km/h	1,350
Max Mach (without external ordnance and stores)	2.00 (1.9**)
G-limit (operational)	9
Maximum flight range (with rockets 2xR-27R1, 2xR-73E launched at half distance):
- at sea level, km	1,270
- at height, km	3,000
- with one refuelling (at 1.500 kg fuel remaining), km	5,200
- with two refuellings in flight, km	8,000
Maximum airborne time (pilot-dependent), hours	10
Takeoff run at normal takeoff weight, m	550
Landing run at normal landing weight (with braking parachute), m	750
Aeroplane dimensions:
- length, m	21.9
- wingspan, m	14.7
- height, m	6.4
Crew	2
In-flight refuelling system
Maximum flow rate (at entry pressure of 3.5 kg/cm 2), l/min	1,100
Powerplant
Number and type of engines	2 x AL-31F (2 x AL-31FP***)
Thrust in afterburner, kgf	12,500 -2 %
Avionics
1. Fire control system
1.1. Air-to-air fire control system
1.1.1. Search and track radar
1.1.2. IRST and laser rangefinder
1.1.2.1. Optical search and track station
1.1.2.2. Helmet-mounted target designator
1.1.3. Wide-angle HUD
1.1.4. IFF system interrogator
1.2. Air-to-surface fire control system
1.2.1. Coloured multi-purpose LCD indicators
1.2.2. Onboard digital computer
1.2.3. GPS satellite-based navigation system
1.2.4. Weapons control system
2. Aeroplane remote control system
3. IFF system transponder
4. Antenna feed system
5. Flight navigation system
5.1. Digital computer
5.2. Attitude and heading reference system
5.3. Short-range radiotechnical navigation system
5.4. GPS system
5.5. Autopilot system
5.6. Altitude and speed data processing and display system
5.7. Air data system
6. Electronic countermeasure equipment
6.1. Radar warning receiver with an expansion block
6.2. Chaff and heat flare dispenser
6.3. Radio jamming transmitter (in pod)
7. Communications system
7.1. VHF and UHF band communications transceiver
7.2. VHF and UHF band communications transceiver
7.3. SW band radio communications transceiver
8. Onboard automatic control system
8.1. Integrated onboard control and crew warning system
8.2. Flight information recording equipment
8.3. Onboard emergency situation warning equipment
9. Video recording system
9.1. Onboard video recorder
9.2. Forward vision video camera
9.3. Video controller
10. Aircraft responder
11. Telecommand homing system
12. Pod-type IRST and laser rangefinder
Limits
Aircraft limit:
- SLL, hours	3,000
- to first overhaul, hours	1,500
- service life, years	25
Engine and outboard accessory-gearbox life:
- to first overhaul, hours	500
- service life limit, hours	1,500