F-35 Lightning II

No fighter in the history of military aviation comes close to the Lockheed Martin F-35 Lightning II joint strike fighter – a truly transformational weapon system that provides quantum leaps in survivability and lethality.

Features of F-35 Lightning II

· Brings stealth capability that is integrated throughout the aircraft with embedded antennas, aligned edges and special coatings and materials.

· Meets multiple service requirements with a single-engine supersonic multi-role fighter.

· Conducts air-to-air and air-to-ground combat missions simultaneously with near impunity.

· Carries a comprehensive sensor package that integrates vast amounts of battle space information with allied forces in the air, on the ground, at sea or in space.

Variants:

The Lightning II will be featured in three principle designs, each maintaining external similarities but differing in dedicated roles. The F-35A model is the true Conventional Take-Off and Landing (CTOL) variant model, operating from runways in the traditional role. The F-35B is the Short Take-Off and Vertical Landing (STOVL) derivative in the series, operating in the role most closely associated with the AV-8B Harrier II system. The F-35C model is a dedicated carrier-based (CV) model designed specifically for operations on aircraft carriers that require their systems to feature strengthened internal structures and landing gear and space-saving capabilities.

Requirement:

USAF F-35A air-to-ground strike aircraft, replacing F-16 and A-10, complementing F-22 (1763); USMC F-35B – STOVL strike fighter to replace F/A-18B/C and AV-8B (480); UK RN F-35C – STOVL strike fighter to replace Sea Harriers (60); US Navy F-35C – first-day-of-war strike fighter to replace F/A-18B/C and A-6, complementing the F/A-18E/F (480 aircraft).

Product Life Cycle:

In October 2001, an international team led by Lockheed Martin was awarded the contract to build JSF. In April 2003, JSF completed a successful preliminary design review (PDR). The critical design review (CDR) for the F-35A was completed in February 2006, for the F-35B in October 2006 and for the F-35C in June 2007. The first flight of the CTOL F-35A took place on 15 December 2006. Low-rate initial production (LRIP) for the F-35A/B was approved in April 2007 with an order for two CTOL aircraft. An LRIP 2 contract for six CTOL aircraft was placed in July 2007. The STOVL F-35B was rolled out in December 2007 and made its first flight, a conventional take-off and landing, in June 2008. STOVL flights are to begin in early 2009. An LRIP contract for six F-35B STOVL aircraft was placed in July 2008.

The F-35C is scheduled for first flight in mid-2009. The F-35A fighter is expected to enter service in 2010, the F-35B in 2012.

The first flight of the F-35 powered by the GE Rolls-Royce F136 engine is scheduled for 2010 with first production engine deliveries in 2012. Critical design review was completed in February 2008.

By the end of 2006, Australia, Canada, the Netherlands and the UK had signed the MoU for the F-35 Production, Sustainment and Follow-on Development (PSFD) phase.

Norway and Turkey (requirement 100 F-35A) signed in January 2007. Denmark and Italy (requirement 131 F-35A and B) signed in February 2007. In May 2008, Israel requested the sale of 25 F-35A aircraft with 50 options.

Participating nations are to sign up to the initial operation test and evaluation (IOT&E) phase by the end of February 2009. In October 2008, Italy announced that it intended not to participate in the IOT&E.

The Lockheed Martin JSF team includes Northrop Grumman, BAE Systems, Pratt and Whitney and Rolls-Royce. Final assembly of the aircraft will take place at Lockheed Martin's Fort Worth plant in Texas.

Major subassemblies will be produced by Northrop Grumman Integrated Systems at El Segundo, California and BAE Systems at Samlesbury, Lancashire, England. BAE Systems is responsible for the design and integration of the aft fuselage, horizontal and vertical tails and the wing-fold mechanism for the CV variant, using experience from the Harrier STOVL programme. Terma of Denmark and Turkish Aerospace Industries of Turkey are supplying sub-assemblies for the centre fuselage.

Unit cost US$ 83 million

Specifications:

Dimensions:

Length: 50.43ft (15.37m)
Width:34.94ft (10.65m)
Height: 17.32ft (5.28m)

Structure:

Accommodation: 1
Hardpoints: 4
Empty Weight: 26,455lbs (12,000kg)
MTOW: 59,966lbs (27,200kg)

Performance:

Max Speed: 1,200mph (1,931kmh; 1,043kts)
Max Range: 1,367miles (2,200km)
Rate-of-Climb: Classified
Service Ceiling: 50,000ft (15,240m; 9.5miles)

Powerplant:

Engine(s): 1 x Pratt & Whitney F135 F119-PW-100 turbofan generating 40,000lbs thrust with afterburn with General Electric GE F120 alternate core engine.

Armament Suite:

1 x GAU-12/U 25mm cannon (F-35A only)

Internal Bay Provision for:
6 x AIM-120C AMRAAM air-to-air missiles OR 2 x 2,000lb JDAM bombs AND 2 x AIM-120C AMRAAM missile

External Provision:
Four external hardpoints for up to 5,000lbs of stores.

AIM-120 AMRAAMs can be substituted with the AIM-9 Sidewinder or AIM-132 ASRAAM systems.