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F-22 Raptor : Air Superiority Fighter

F-22 Raptor is a single-seat, twin-engine fifth-generation supermaneuverable fighter aircraft that uses stealth technology. It was designed primarily as an air superiority fighter, but has additional capabilities that include ground attack, electronic warfare, and signals intelligence roles. Lockheed Martin Aeronautics is the prime contractor and is responsible for the majority of the airframe, weapon systems and final assembly of the F-22. Program partner Boeing Defense, Space & Security provides the wings, aft fuselage, avionics integration, and training systems.

The aircraft was variously designated F-22 and F/A-22 during the years prior to formally entering USAF service in December 2005 as the F-22A. Despite a protracted and costly development period, the United States Air Force considers the F-22 a critical component of US tactical air power, and claims that the aircraft is unmatched by any known or projected fighter, while Lockheed Martin claims that the Raptor's combination of stealth, speed, agility, precision and situational awareness, combined with air-to-air and air-to-ground combat capabilities, makes it the best overall fighter in the world today. Air Chief Marshal Angus Houston, former Chief of the Australian Defence Force, said in 2004 that the "F-22 will be the most outstanding fighter plane ever built."

The high cost of the aircraft, a lack of clear air-to-air combat missions because of delays in the Russian and Chinese fifth-generation fighter programs, a US ban on Raptor exports, and the ongoing development of the planned cheaper and more versatile F-35 resulted in calls to end F-22 production. In April 2009 the US Department of Defense proposed to cease placing new orders, subject to Congressional approval, for a final procurement tally of 187 Raptors. The National Defense Authorization Act for Fiscal Year 2010 lacked funding for further F-22 production.

The production F-22 model was unveiled on 9 April 1997 at Lockheed Georgia Co., Marietta, Georgia. It first flew on 7 September 1997. The first production F-22 was delivered to Nellis Air Force Base, Nevada, on 7 January 2003. In 2006, the Raptor's development team, composed of Lockheed Martin and over 1,000 other companies, plus the United States Air Force, won the Collier Trophy, American aviation's most prestigious award. In 2006, the USAF sought to acquire 381 F-22s, to be divided among seven active duty combat squadrons and three integrated Air Force Reserve Command and Air National Guard squadrons. Several design changes were made from the YF-22 for production. The swept-back angle on the wing's leading edge was decreased from 48° to 42°, while the vertical stabilizer area was decreased by 20%. To improve pilot visibility, the canopy was moved forward 7 inches (178 mm), and the engine intakes were moved rearward 14 inches (356 mm). The shape of the wing and stabilator trailing edges was refined to improve aerodynamics, strength, and stealth characteristics. Also, the vertical stabilizer was shifted rearward.

F-22 production was split up over many subcontractors across 46 states, in a strategy to increase Congressional support for the program. However the production split, along with the use of several new technologies were likely responsible for increased costs and delays. Many capabilities were deferred to post-service upgrades, reducing the initial cost but increasing total project cost. Each aircraft required "1,000 subcontractors and suppliers and 95,000 workers" to build. The F-22 was in production for 15 years, at a rate of roughly two per month.

Two F-22s overflying snow-capped mountains.

Two F-22s during flight testing, the upper one being the first EMD F-22, "Raptor 01". The United States Air Force originally planned to order 750 ATFs at a cost of $26.2 billion, with production beginning in 1994; however, the 1990 Major Aircraft Review led by Defense Secretary Dick Cheney altered the plan to 648 aircraft beginning in 1996. The goal changed again in 1994, when it became 438 aircraft entering service in 2003 or 2004, but a 1997 Department of Defense report put the purchase at 339. In 2003, the Air Force said that the existing congressional cost cap limited the purchase to 277. By 2006, the Pentagon said it will buy 183 aircraft, which would save $15 billion but raise the cost of each aircraft, this was implemented in the form of a multi-year procurement plan, which allowed for further orders later. The total cost of the program by 2006 was $62 billion. In April 2006, the cost of the F-22 was assessed by the Government Accountability Office to be $361 million per aircraft. By April 2006, $28 billion had been invested in F-22 development and testing; while the Unit Procurement Cost was estimated at $177.6 million in 2006, based on a production run of 181 airframes. It was estimated by the end of production, $34 billion will have been spent on procurement, resulting in a total program cost of $62 billion, around $339 million per aircraft. The incremental cost for an additional F-22 was estimated as about $138 million.

Two F-22 Raptors line up for refueling during their first official deployment, October 2005. On 31 July 2007, Lockheed Martin received a multi-year contract for 60 F-22s worth a total of $7.3 billion. The contract brought the number of F-22s on order to 183 and extended production through 2011. To restart production would be very costly; the cost for another 75 aircraft was estimated in 2009 to be an extra $70 million per unit.

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Rafale, The Fighter from French

Rafale is a twin-jet combat aircraft capable of carrying out a wide range of short and long-range missions, including ground and sea attack, air defence and air superiority, reconnaissance, and high-accuracy strike or nuclear strike deterrence. The aircraft were developed for the French Air Force and Navy. The French Air Force and Navy ordered 294 (234 for the air force and 60 for the navy); 82 aircraft had been delivered by the end of 2009. The Rafale entered into service with French Navy in December 2000, and with the French Air Force in 2004. Ten aircraft are operational on the Charles de Gaulle aircraft carrier. Rafale B and C entered service with the French Air Force in June 2006, when the first squadron was established. The second air force squadron was set up in 2008. Navy Rafale F1 standard fighters have air-to-air capability. Deliveries to the navy of the F2 standard, with air-to-ground missiles, began in May 2006 and 17 were delivered in May 2008. F1 aircraft are to be upgraded. A €3.1bn ($3.89bn) contract to develop the fully capable F3 standard aircraft was awarded to Dassault Aviation (€1.5bn), Snecma (€600m), Thales (€500m) and other French defence contractors by French Ministry of Defence in February 2004. An order for 59 F3 aircraft, 47 for the air force (11 two-seat and 36 single-seat) and 12 (single-seat) for the navy, was placed in December 2004. The Rafale F3 was certified in July 2008. The contract also includes the upgrade of Rafale F2 aircraft.

In March 2007, three French Air Force and three Navy Rafale fighters were deployed in Tajikistan in support of the Nato International Security Assistance Force (ISAF) in Afghanistan. The French Government ordered 60 additional Rafale aircraft in November 2009. The Brazilian Government awarded a $4bn contract to Dassault Aviation in January 2010 to supply 36 Rafale multirole aircraft. The UAE will acquire the Rafale at a cost of about €2bn ($2.4bn) to replace its 60 aging Mirage fighters.

Cockpit

The cockpit has hands-on throttle and stick control (HOTAS). The cockpit is equipped with a head-up, wide-angle holographic display from Thales Avionique, which provides aircraft control data, mission data and firing cues. A collimated, multi-image head-level display presents tactical situation and sensor data, and two touch-screen lateral displays show the aircraft system parameters and mission data. The pilot also has a helmet-mounted sight and display. A CCD camera and on-board recorder records the image of the head-up display throughout the mission.

Weapons

The Rafale can carry payloads of over 9t on 14 hardpoints for the air force version, and 13 for the naval version. The range of weapons includes: Mica, Magic, Sidewinder, ASRAAM and AMRAAM air-to-air missiles; Apache, AS30L, ALARM, HARM, Maverick and PGM100 air-to-ground missiles; and Exocet / AM39, Penguin 3 and Harpoon anti-ship missiles. For a strategic mission the Rafale can deliver the MBDA (formerly Aerospatiale) ASMP stand-off nuclear missile. In December 2004, the MBDA Storm Shadow / Scalp EG stand-off cruise missile was qualified on the Rafale.

In September 2005, the first flight of the MBDA Meteor BVRAAM beyond visual range air-to-air missile was conducted on a Rafale fighter. In December 2005, successful flight trials were carried out from the Charles de Gaulle of the range of Rafale's weapon systems – Exocet, Scalp-EG, Mica, ASMP-A (to replace the ASMP) and Meteor missiles. In April 2007, the Rafale carried out the first firing of the Sagem AASM (armement air-sol modulaire - air-to-groung modular weapon) precision-guided bomb, which has both GPS / inertial guidance and, optionally, imaging infrared terminal guidance. Rafale have been equipped with the AASM from 2008. Rafale can carry six AASM misssiles, with each aiming to hit the target with 10m accuracy. The Rafale has a twin gun pod and a Nexter (formerly Giat) 30mm DEFA 791B cannon, which can fire 2,500 rounds a minute. The Rafale is equipped with laser designation pods for laser guidance of air-to-ground missiles.

Countermeasures

The Rafale's electronic warfare system is the Spectra from Thales. Spectra incorporates solid state transmitter technology, radar warner, DAL laser warning receiver, missile warning, detection systems and jammers.

Sensors

The Rafale is equipped with an RBE2 passive electronically scanned radar developed by Thales which has look down and shoot down capability. The radar can track up to eight targets simultaneously and provides threat identification and prioritisation. Thales is developing an active electronically scanned version of the RBE2 which will equip the Rafale from 2011. Flight tests of the radar onboard the Rafale took place in 2008. RUAG Aviation has been awarded a $5m contract by Thales in May 2009 to produce sub assemblies for the RBE2 radar to be equipped in the Rafale fighter jet. It will build wired-back structures linking the individual modules together and connecting the radar to the airframe. The optronic systems include the Thales / SAGEM OSF infrared search and track system, installed in the nose of the aircraft. The optronic suite carries out search, target identification, telemetry and automatic target discrimination and tracking.

Navigation and communications

The communications suite on the Rafale uses the Saturn onboard V/UHF radio, which is a second-generation, anti-jam tactical UHF radio for Nato. Saturn provides voice encryption in fast-frequency hopping mode. The aircraft is also equipped with fixed-frequency VHF/UHF radio for communications with civil air traffic control. A multifunction information distribution system (MIDS) terminal provides secure, high-data-rate tactical data exchange with NATO C2 stations, AWACS aircraft or naval ships. Rafale is equipped with a Thales TLS 2000 navigation receiver, which is used for the approach phase of flight. The TLS 2000 integrates the instrument landing system (ILS), microwave landing system (MLS) and VHF omni-directional radio-ranger (VOR) and marker functions. The radar altimeter is the AHV 17 altimeter from Thales, which is suitable for very low flight. The Rafale has a TACAN tactical air navigation receiver for en route navigation and as a landing aid. The Rafale has an SB25A combined interrogator-transponder developed by Thales. The SB25A is the first IFF using electronic scanning technology.

Engine

The Rafale is powered by two M88-2 engines from SNECMA, each providing a thrust of 75kN. The aircraft is equipped for buddy-buddy refuelling with a flight refuelling hose reel and drogue pack. The first M88 engine was delivered in 1996. It is a twin-shaft bypass turbofan engine principally suitable for low-altitude penetration and high-altitude interception missions. The M88 incorporates the latest technologies such as single-piece bladed compressor disks (blisks), an on-polluting combustion chamber, single-crystal high-pressure turbine blades, powder metallurgy disks, ceramic coatings and composite materials. The M88 engine comprises a three-stage LP compressor with inlet guide vane, an annular combustion chamber, single-stage cooled HP turbine, single-stage cooled LP turbine, radial A/B chamber, variable-section convergent flap-type nozzle and full authority digital engine control (FADEC). Messier-Dowty provides the "jumper" landing gear, designed to spring out when the aircraft is catapulted by the nose gear strut.

Lockheed Martin F-35 Lightning II

The Lockheed Martin F-35 Lightning II is a family of single-seat, single-engine, fifth generation multirole fighters under development to perform ground attack, reconnaissance, and air defense missions with stealth capability. The F-35 has three main models; the F-35A is a conventional takeoff and landing variant, the F-35B is a short take off and vertical-landing variant, and the F-35C is a carrier-based variant.

The F-35 is descended from the X-35, the product of the Joint Strike Fighter (JSF) program. JSF development is being principally funded by the United States, with the United Kingdom and other partner governments providing additional funding. The partner nations are either NATO members or close U.S. allies. It is being designed and built by an aerospace industry team led by Lockheed Martin. The F-35 carried out its first flight on 15 December 2006.

The United States plans to buy a total of 2,443 aircraft to provide the bulk of its tactical airpower for the U.S. Air Force, Marine Corps and Navy over the coming decades. The United Kingdom, Italy, Netherlands, Australia, Canada, Norway, Denmark, Turkey, Israel and Japan are part of the development program and may equip their air services with the F-35.

Design

The F-35 has a maximum speed of over Mach 1.6. With a maximum takeoff weight of 60,000 lb (27,000 kg), the Lightning II is considerably heavier than the lightweight fighters it replaces. In empty and maximum gross weights, it more closely resembles the single-seat, single-engine Republic F-105 Thunderchief, which was the largest single-engine fighter of the Vietnam war era. The F-35's modern engine delivers over 60 percent more thrust in an aircraft of the same weight so that in thrust to weight and wing loading it is much closer to a comparably equipped F-16. Acquisition deputy to the assistant secretary of the air force, Lt. Gen. Mark D. "Shack" Shackelford has said that the F-35 is designed to be America's "premier surface-to-air missile killer and is uniquely equipped for this mission with cutting edge processing power, synthetic aperture radar integration techniques, and advanced target recognition."

Some improvements over current-generation fighter aircraft are: Durable, low-maintenance stealth technology, using structural fiber mat instead of the high-maintenance coatings of legacy stealth platforms; Integrated avionics and sensor fusion that combine information from off- and on-board sensors to increase the pilot's situational awareness and improve target identification and weapon delivery, and to relay information quickly to other command and control (C2) nodes; High speed data networking including IEEE 1394b and Fibre Channel. (Fibre Channel is also used on Boeing's Super Hornet.

The Autonomic Logistics Global Sustainment (ALGS), Autonomic Logistics Information System (ALIS) and Computerized Maintenance Management System (CMMS) are claimed to help ensure aircraft uptime with minimal maintenance manpower.[168] However the Pentagon has moved to open the sustainment for competitive bidding by other companies. This was after Lockheed admitted that instead of costing twenty percent less than the F-16 per flight hour, the F-35 would actually cost twelve percent more.

Lockheed Martin claims the F-35 is intended to have close and long-range air-to-air capability second only to that of the F-22 Raptor. The company has suggested that the F-35 could also replace the USAF's F-15C/D fighters in the air superiority role and the F-15E Strike Eagle in the ground attack role, but it does not have the range or payload of either F-15 model. The F-35A does carry a similar air-to-air armament as the conceptual Boeing F-15SE Silent Eagle when both aircraft are configured for low observable operations and has over 80 percent of the larger aircraft's combat radius, under those conditions.

Lockheed Martin has said that the F-35 has the advantage over the F-22 in basing flexibility and "advanced sensors and information fusion". The majority of the structural composites in the F-35 are made out of bismaleimide (BMI) and composite epoxy material. However the F-35 will be the first mass produced aircraft to include structural nanocomposites, namely carbon nanotube reinforced epoxy.

The F-35 program has learned from the corrosion problems that the F-22 had when it was first introduced in 2005. The F-35 uses a gap filler that causes less galvanic corrosion to the skin, is designed with fewer gaps in its skin that require gap filler, and has better drainage.

A United States Navy study found that the F-35 will cost 30 to 40 percent more to maintain than current jet fighters. A Pentagon study found that it may cost $1 trillion to maintain the entire fleet over its lifetime. The relatively short 35 foot wingspan of the A and B variants is set by the F-35B's requirement to fit inside the Navy's current amphibious assault ship elevators. The F-35C's longer wing is considered to be more fuel efficient.

Engines

The Lift System is composed of a lift fan, drive shaft, two roll posts and a "Three Bearing Swivel Module" (3BSM). The 3BSM is a thrust vectoring nozzle which allows the main engine exhaust to be deflected downward at the tail of the aircraft. The lift fan is near the front of the aircraft and provides a counterbalancing thrust using two counter-rotating blisks. It is powered by the engine's low-pressure (LP) turbine via a drive shaft and gearbox. Roll control during slow flight is achieved by diverting unheated engine bypass air through wing-mounted thrust nozzles called Roll Posts. Like lift engines, the added lift fan machinery increases payload capacity during vertical flight, but is dead weight during horizontal flight. The cool exhaust of the fan also reduces the amount of hot, high-velocity air that is projected downward during vertical take off, which can damage runways and aircraft carrier decks.

To date, F136 funding has come at the expense of other parts of the program, reducing the number of aircraft built and increasing their costs. The F136 team has claimed that their engine has a greater temperature margin which may prove critical for VTOL operations in hot, high altitude conditions. Pratt & Whitney is also testing higher thrust versions of the F135, partly in response to GE's claims that the F136 is capable of producing more thrust than the 43,000 lbf (190 kN) supplied by early F135s. The F135 has demonstrated a maximum thrust of over 50,000 lbf (220 kN) during testing. The F-35's Pratt & Whitney F135 is the most powerful engine ever installed in a fighter aircraft. The F135 is the second (radar) stealthy afterburning jet engine and like the Pratt & Whitney F119 from which it was derived, has suffered from pressure pulsations in the afterburner at low altitude and high speed or "screech". In both cases this problem was fixed during development of the fighter program. Turbine bearing health in the engine will be monitored with thermoelectric powered wireless sensors.

Armament

The F-35A includes a GAU-22/A, a four-barrel version of the GAU-12 Equalizer 25 mm cannon. The cannon is mounted internally with 182 rounds for the F-35A or in an external pod with 220 rounds for the F-35B and F-35C. The gun pod for the B and C variants will have stealth features. The Terma A/S multi-mission pod (MMP) could be used for different equipment in the future for all three variants, such as electronic warfare equipment, reconnaissance equipment, or possibly a rearward-facing radar.

It has two internal weapons bays, and external hardpoints that can mount four underwing pylons and two near wingtip pylons. The two outer hardpoints can only carry pylons for the AIM-9X Sidewinder and AIM-132 ASRAAM short-range air-to-air missiles (AAM). The other pylons can carry the AIM-120 AMRAAM BVR AAM, Storm Shadow air-launched cruise missile, AGM-158 Joint Air to Surface Stand-off Missile (JASSM) cruise missile, and guided bombs. The external pylons can carry missiles, bombs, and fuel tanks at the expense of reduced stealth. An air-to-air load of eight AIM-120s and two AIM-9s is possible using internal and external weapons stations; a configuration of six 2,000 lb (910 kg) bombs, two AIM-120s and two AIM-9s can also be arranged.

Internally, up to two 2,000 lb (910 kg) air-to-ground bombs can be carried in A and C models (two 1,000 lb (450 kg) bombs in the B model,) along with two smaller weapons, normally expected to be air-to-air missiles. The weapon bays can carry AIM-120 AMRAAM, AIM-132 ASRAAM, the Joint Direct Attack Munition (JDAM) – up to 2,000 lb (910 kg), the Joint Stand off Weapon (JSOW), Brimstone anti-armor missiles, and Cluster Munitions (WCMD).

Lockheed Martin states that the weapons load can also be configured as all-air-to-ground or all-air-to-air, and has suggested that a Block 5 version will be able to carry three internal weapons per bay instead of two, replacing the heavy bomb with two smaller weapons such as AIM-120 AMRAAM air-to-air missiles. Upgrades include up to four GBU-39 Small Diameter Bombs (SDB) in each bay (three per bay in F-35B, or four GBU-53/B in each bay for all F-35 variants; The MBDA Meteor air-to-air missile is currently being adapted to fit four internally in the missile spots and may be integrated into the F-35. A modified Meteor design with smaller tailfins for the F-35 was revealed in September 2010. The United Kingdom had originally planned to put up to four AIM-132 ASRAAM internally but this has been changed to carry 2 internal and 2 external ASRAAMs. The external ASRAAMs are planned to be carried on "stealthy" pylons to increase the F-35's radar cross section slightly; the missile allow attacks to slightly beyond visual range without using radar that might alert the target.

Norway and Australia are funding a program to adapt the Naval Strike Missile (NSM) to fit the internal bays of the F-35. This will be a multi-role version, named the Joint Strike Missile (JSM), and will be the only cruise missile to fit the internal bays. Studies have shown that the F-35 would be able to carry two of these internally, while four additional missiles could be carried externally. The missile has an expected range in excess of 150 nmi (278 km).

Solid-state lasers were being developed as optional weapons for the F-35 as of 2002. The F-35 is expected to take on the Wild Weasel mission, but there are no planned anti-radiation missiles for internal stealthy carriage. The B61 nuclear bomb was scheduled for deployment in 2017, but delays in the F-35 program may delay this. It is now expected to be deployable in the early 2020s.

Cockpit

The F-35 features a full-panel-width "panoramic cockpit display" (PCD) glass cockpit, with dimensions of 20 by 8 inches (50 by 20 centimeters). A cockpit speech-recognition system (Direct Voice Input) provided by Adacel is planned to improve the pilot's ability to operate the aircraft over the current-generation interface. The F-35 will be the first U.S. operational fixed-wing aircraft to use this system, although similar systems have been used in AV-8B and trialled in previous U.S. jets, particularly the F-16 VISTA.

A helmet-mounted display system (HMDS) will be fitted to all models of the F-35. A helmet-mounted cueing system is already in service with the F-15s, F-16s and F/A-18s. While some fighters have offered HMDS along with a head up display (HUD), this will be the first time in several decades that a front line tactical jet fighter has been designed without a HUD. The F-35 is equipped with a right-hand HOTAS side stick controller. The Martin-Baker US16E ejection seat is used in all F-35 variants. The US16E seat design balances major performance requirements, including safe-terrain-clearance limits, pilot-load limits, and pilot size. It uses a twin-catapult system that is housed in side rails. The F-35 uses a derivative version of the oxygen system that has been implicated in hypoxia incidents on board the F-22. But the F-35 does not fly as high or as fast as the F-22; its flight profile is similar to other fighters that use such systems routinely.

Sensors and Avionics

The F-35's sensor and communications suite is intended to facilitate situational awareness, command-and-control and network-centric warfare capability. The main sensor on board the F-35 is its AN/APG-81 AESA-radar, designed by Northrop Grumman Electronic Systems. It is augmented by the Electro-Optical Targeting System (EOTS) mounted under the nose of the aircraft, designed by Lockheed Martin. This gives the same capabilities as the Lockheed Martin Sniper XR while avoiding making the aircraft more easily detectable.

Six additional passive infrared sensors are distributed over the aircraft as part of Northrop Grumman's AN/AAQ-37 distributed aperture system (DAS), which acts as a missile warning system, reports missile launch locations, detects and tracks approaching aircraft spherically around the F-35, and replaces traditional night vision goggles for night operations and navigation. All DAS functions are performed simultaneously, in every direction, at all times. The F-35's Electronic Warfare systems are designed by BAE Systems and include Northrop Grumman components. Some functions such as the Electro-Optical Targeting System and the Electronic Warfare system are not usually found integrated on fighters.

The AN/ASQ-239 (Barracuda) system is an improved version of the AN/ALR-94 EW suite on the F-22. The AN/ASQ-239 provides sensor fusion of RF and IR tracking functions, basic radar warning, multispectral countermeasures for self-defense against threat missiles, situational awareness and electronic surveillance. It uses 10 RF antennae over the leading and trailing edges of the wing leading and trailing edges of the horizontal tail.

The communications, navigation and identification (CNI) suite is designed by Northrop Grumman and includes the Multifunction Advanced Data Link (MADL). The F-35 will be the first jet fighter that has sensor fusion that combines both radio frequency and IR tracking for continuous target detection and identification in all directions which is shared via MADL to other platforms without compromising low observability. However the F-35 also includes the non-stealthy Link 16 for communications with legacy systems for missions including Close air support. The F-35 has been designed with synergy between sensors as a specific requirement, with the "senses" of the aircraft expected to provide a more cohesive picture of the reality around it, and be available in principle for use in any possible way, and any possible combination with one another. All of the sensors feed directly into the main processors to support the entire mission of the aircraft. For example the AN/APG-81 functions not just as a multi-mode radar, but also as part of the aircraft's electronic warfare system. Northrop Grumman is offering the APG-81 as an upgrade for legacy aircraft, but because the "back end processing" on the F-35 is done in software on the main processors, the upgrade version requires their Scalable Agile Beam Radar electronics to operate on other aircraft.

Unlike previous aircraft, such as the F-22, all software for the F-35 is written in C++ for faster code development. The Integrity DO-178B real-time operating system (RTOS) from Green Hills Software runs on COTS Freescale PowerPC processors. The final Block 3 software for the F-35 is planned to have 8.6 million lines of software code. The scale of the program has led to a software crisis as officials continue to discover that additional software needs to be written.[258] General Norton Schwartz has said that the software is the biggest factor that might delay the USAF's initial operational capability which is now scheduled for April 2016. Michael Gilmore, Director of Operational Test & Evaluation, has written that, "the F-35 mission systems software development and test is tending towards familiar historical patterns of extended development, discovery in flight test, and deferrals to later increments."

The F-35's electronic warfare systems are intended to detect hostile aircraft first, which can then be scanned with the electro-optical system and action taken to engage or evade the opponent before the F-35 is detected. The CATbird avionics testbed for the F-35 program has proved capable of detecting and jamming F-22 radars. The F-35 was previously considered a platform for the Next Generation Jammer, but attention has shifted to the use of unmanned platforms.

Helmet-mounted display system

The F-35 does not need to be physically pointing at its target for weapons to be successful. This is possible because of sensors that can track and target a nearby aircraft from any orientation, provide the information to the pilot through his helmet (and therefore visible no matter which way they are looking), and provide the seeker-head of a missile with sufficient information. Recent missile types provide a much greater ability to pursue a target regardless of the launch orientation, called "High Off-Boresight" capability, although the speed and direction in which the munition is launched affect the effective range of the weapon. Sensors use combined radio frequency and infra red (SAIRST) to continually track nearby aircraft while the pilot's helmet-mounted display system (HMDS) displays and selects targets. The helmet system replaces the display suite-mounted head-up display used in earlier fighters.

The F-35's systems provide the edge in the "observe, orient, decide, and act" OODA loop; stealth and advanced sensors aid in observation (while being difficult to observe), automated target tracking helps in orientation, sensor fusion simplifies decision making, and the aircraft's controls allow the pilot to keep their focus on the targets, rather than the controls of their aircraft.

The problems with the current Vision Systems International helmet-mounted display led Lockheed Martin to issue a draft specification for proposals for an alternative on 1 March 2011. The alternative system will be based on Anvis-9 night vision goggles. It will be supplied by BAE systems. The BAE system does not yet include all the features of the VSI helmet and if successful will have the remaining features incorporated. Use of the BAE system would also require a cockpit redesign,

In 2011, Lockheed granted VSI a contract to fix the vibration, jitter, night-vision and sensor display problems in their helmet-mounted display. The improved displays are expected to be delivered in third quarter of 2013. One of the potential improvements is to replace Intevac’s ISIE-10 day/night camera located in the helmet with their ISIE-11 model which will improve the resolution from 1280x1024 to 1600x1200 pixels.

Maintenance

The program's maintenance concept is for any F-35 to be maintained in any F-35 maintenance facility and that all F-35 parts in all bases will be globally tracked and shared as needed. The commonality between the different variants has allowed the USMC to create their first aircraft maintenance Field Training Detachment to directly apply the lessons of the USAF to their own F-35 maintenance operations.

The aircraft has been designed for ease of maintenance, with 95% of all field replaceable parts "one deep" where nothing else has to be removed to get to the part in question. For instance the ejection seat can be replaced without removing the canopy, the aircraft uses low-maintenance electro-hydrostatic actuators instead of hydraulic systems and an all-composite skin without the fragile coatings found on earlier stealth aircraft.

F/A-18 Hornet

F/A-18 Hornet is a twin-engine supersonic, all-weather carrier-capable multirole fighter jet, designed to dogfight and attack ground targets (F/A for Fighter/Attack). Designed by McDonnell Douglas and Northrop, the F/A-18 was derived from the latter's YF-17 in the 1970s for use by the United States Navy and Marine Corps. The Hornet is also used by the air forces of several other nations. It has been the aerial demonstration aircraft for the U.S. Navy's Flight Demonstration Squadron, the Blue Angels, since 1986. The F/A-18 has a top speed of Mach 1.8. It can carry a wide variety of bombs and missiles, including air-to-air and air-to-ground, supplemented by the 20 mm M61 Vulcan cannon. It is powered by two General Electric F404 turbofan engines, which give the aircraft a high thrust-to-weight ratio. The F/A-18 has excellent aerodynamic characteristics, primarily attributed to its leading edge extensions (LEX). The fighter's primary missions are fighter escort, fleet air defense, Suppression of Enemy Air Defenses (SEAD), air interdiction, close air support and aerial reconnaissance. Its versatility and reliability have proven it to be a valuable carrier asset, though it has been criticized for its lack of range and payload compared to its earlier contemporaries, such as the Grumman F-14 Tomcat in the fighter and strike fighter role, and the Grumman A-6 Intruder and LTV A-7 Corsair II in the attack role. The F/A-18 Hornet provided the baseline design for the Boeing F/A-18E/F Super Hornet, a larger, evolutionary redesign of the F/A-18. Compared to the Hornet, the Super Hornet is larger, heavier and has improved range and payload. The F/A-18E/F was originally proposed as an alternative to an all-new aircraft to replace existing dedicated attack aircraft such as the A-6. The larger variant was also directed to replace the aging F-14 Tomcat, thus serving a complementary role with Hornets in the U.S. Navy, and serving a wider range of roles including refueling tanker, and electronic jamming platform.

Design

The F/A-18 is a twin engine, mid-wing, multi-mission tactical aircraft. It is highly maneuverable, owing to its good thrust to weight ratio, digital fly-by-wire control system, and leading edge extensions (LEX). The LEX allow the Hornet to remain controllable at high angles of attack. The wing is a trapezoidal shape with 20-degree sweepback on the leading edge and a straight trailing edge. The wing has full-span leading edge flaps and the trailing edge has single-slotted flaps and ailerons over the entire span. Canted vertical stabilizers are another distinguishing design element, one among several other such elements that enable the Hornet's excellent high angle-of-attack ability include oversized horizontal stabilators, oversized trailing edge flaps that operate as flaperons, large full-length leading edge slats, and flight control computer programming that multiplies the movement of each control surface at low speeds and moves the vertical rudders inboard instead of simply left and right. The Hornet's normally high angle-of-attack performance envelope was put to rigorous testing and enhanced in the NASA F-18 High Alpha Research Vehicle (HARV). NASA used the F-18 HARV to demonstrate flight handling characteristics at high angle-of-attack (alpha) of 65–70 degrees using thrust vectoring vanes. F/A-18 stabilators were also used as canards on NASA's F-15S/MTD.

The Hornet was among the first aircraft to heavily use multi-function displays, which at the switch of a button allow a pilot to perform either fighter or attack roles or both. This "force multiplier" ability gives the operational commander more flexibility to employ tactical aircraft in a fast-changing battle scenario. It was the first Navy aircraft to incorporate a digital multiplex avionics bus, enabling easy upgrades.

The Hornet is also notable for having been designed to reduce maintenance, and as a result has required far less downtime than its heavier counterparts, the F-14 Tomcat and the A-6 Intruder. Its mean time between failure is three times greater than any other Navy strike aircraft, and requires half the maintenance time. Its General Electric F404 engines were also innovative in that they were designed with operability, reliability and maintainability first. The engine, while unexceptional in rated performance, demonstrates exceptional robustness under various conditions and is resistant to stall and flameout. The F404 engine connects to the airframe at only 10 points and can be replaced without special equipment; a four person team can remove the engine within 20 minutes.

The engine air inlets of the Hornet, like that of the F-16, are of a simpler "fixed" design, while those of the F-4, F-14, and F-15 have variable geometry or variable ramp air inlets. This is a speed limiting factor in the Hornet design. Instead, the Hornet uses bleed air vents on the inboard surface of the engine air intake ducts to slow and reduce the amount of air reaching the engine. While not as effective as variable geometry, the bleed air technique functions well enough to achieve near Mach 2 speeds, which is within the designed mission requirements.

A 1989 USMC study found that single seat fighters were well suited to air to air combat missions while dual seat fighters were favored for complex strike missions against heavy air and ground defenses in adverse weather. The question being not so much as to whether a second pair of eyes would be useful, but as to having the second crewman sit in the same fighter or in a second fighter. Single-seat fighters that lacked wingmen were shown to be especially vulnerable

Variants

A/B

The F/A-18A is the single-seat variant and the F/A-18B is the two-seat variant. The space for the two-seat cockpit is provided by a relocation of avionic equipment and a 6% reduction in internal fuel; two-seat Hornets are otherwise fully combat-capable. The B model is used primarily for training. In 1992, the original Hughes AN/APG-65 radar was replaced with the Hughes (now Raytheon) AN/APG-73, a faster and more capable radar. A model Hornets that have been upgraded to the AN/APG-73 are designated F/A-18A+.

C/D

The F/A-18C is the single-seat variant and the F/A-18D is the two-seat variant. The D-model can be configured for training or as an all-weather strike craft. The "missionized" D model's rear seat is configured for a Marine Corps Naval Flight Officer who functions as a Weapons and Sensors Officer to assist in operating the weapons systems. The F/A-18D is primarily operated by the U.S. Marine Corps in the night attack and FAC(A) (Forward Air Controller (Airborne)) roles. The F/A-18C and D models are the result of a block upgrade in 1987 incorporating upgraded radar, avionics, and the capacity to carry new missiles such as the AIM-120 AMRAAM air-to-air missile and AGM-65 Maverick and AGM-84 Harpoon air-to-surface missiles. Other upgrades include the Martin-Baker NACES (Navy Aircrew Common Ejection Seat), and a self-protection jammer. A synthetic aperture ground mapping radar enables the pilot to locate targets in poor visibility conditions. C and D models delivered since 1989 also have improved night attack abilities, consisting of the Hughes AN/AAR-50 thermal navigation pod, the Loral AN/AAS-38 NITE Hawk FLIR (forward looking infrared array) targeting pod, night vision goggles, and two full-color (formerly monochrome) multi-function display (MFDs) and a color moving map.

In addition, 60 D-model Hornets are configured as the night attack F/A-18D (RC) with ability for reconnaissance. These could be outfitted with the ATARS electro-optical sensor package that includes a sensor pod and equipment mounted in the place of the M61 cannon. Beginning in 1992, the F404-GE-402 enhanced performance engine, providing approximately 10% more maximum static thrust became the standard Hornet engine. Since 1993, the AAS-38A NITE Hawk added a designator/ranger laser, allowing it to self-mark targets. The later AAS-38B added the ability to strike targets designated by lasers from other aircraft. Production of the F/A-18C ended in 1999. In 2000, the last F/A-18D was delivered to the U.S. Marine Corps.

E/F Super Hornet

The single-seat F/A-18E and two-seat F/A-18F Super Hornets carry over the name and design concept of the original F/A-18, but have been extensively redesigned. The Super Hornet has a new, 25% larger airframe, larger rectangular air intakes, more powerful GE F414 engines based on F/A-18's F404, and upgraded avionics suite. Like the Marine Corps' F/A-18D, the Navy's F/A-18F carries a Naval Flight Officer as a second crewman in a Weapons Systems Officer (WSO) role. The Super Hornet aircraft is in production and has equipped 22 squadrons.

The EA-18G Growler is an electronic warfare version of the two-seat F/A-18F, which entered production in 2007. The Growler will replace the Navy's EA-6B Prowler and carries a Naval Flight Officer as a second crewman in an Electronic Countermeasures Officer (ECMO) role. Australia is the only nation other than the United States to operate the Super Hornet.

Other US variants

F-18(R)

This was a proposed reconnaissance version of the F/A-18A. It included a sensor package that replaced the 20 mm cannon. The first of two prototypes flew in August 1984. Small numbers were produced.

RF-18D

Proposed two-seat reconnaissance version for the US Marine Corps in the mid-1980s. It was to carry a radar reconnaissance pod. The system was canceled after it was unfunded in 1988. This ability was later realized on the F/A-18D(RC).

TF-18A

Two-seat training version of the F/A-18A fighter, later redesignated F/A-18B.

F-18 HARV

Single-seat High Alpha Research Vehicle for NASA. High angles of attack using thrust vectoring, modifications to the flight controls, and forebody strakes

X-53 Active Aeroelastic Wing

A NASA F/A-18 has been modified to demonstrate the Active Aeroelastic Wing technology, and was designated X-53 in December 2006.

General Dynamics F-16 Fighting Falcon Design

The General Dynamics F-16 Fighting Falcon is a multirole jet fighter aircraft originally developed by General Dynamics for the United States Air Force (USAF). Designed as an air superiority day fighter, it evolved into a successful all-weather multirole aircraft. Over 4,400 aircraft have been built since production was approved in 1976. Although no longer being purchased by the U.S. Air Force, improved versions are still being built for export customers. In 1993, General Dynamics sold its aircraft manufacturing business to the Lockheed Corporation, which in turn became part of Lockheed Martin after a 1995 merger with Martin Marietta.

The Fighting Falcon is a fighter with numerous innovations including a frameless bubble canopy for better visibility, side-mounted control stick to ease control while maneuvering, a seat reclined 30 degrees to reduce the effect of g-forces on the pilot, and the first use of a relaxed static stability/fly-by-wire flight control system that makes it a highly nimble aircraft. The F-16 has an internal M61 Vulcan cannon and has 11 hardpoints for mounting weapons and other mission equipment. Although the F-16's official name is "Fighting Falcon", it is known to its pilots as the "Viper", due to a perceived resemblance to a viper snake as well as after the Battlestar Galactica Colonial Viper starfighter.

In addition to active duty U.S. Air Force, Air Force Reserve Command, and Air National Guard units, the aircraft is also used by the USAF aerial demonstration team, the U.S. Air Force Thunderbirds, and as an adversary/aggressor aircraft by the United States Navy. The F-16 has also been procured to serve in the air forces of 25 other nations.

Design

The F-16 is a single-engined, very maneuverable, supersonic, multi-role tactical aircraft. The F-16 was designed to be a cost-effective combat "workhorse" that can perform various kinds of missions and maintain around-the-clock readiness. It is much smaller and lighter than its predecessors, but uses advanced aerodynamics and avionics, including the first use of a relaxed static stability/fly-by-wire (RSS/FBW) flight control system, to achieve enhanced maneuver performance. Highly nimble, the F-16 can pull 9-g maneuvers and can reach a maximum speed of over Mach 2.

The Fighting Falcon includes innovations such as a frameless bubble canopy for better visibility, side-mounted control stick, and reclined seat to reduce g-force effects on the pilot. The F-16 has an internal M61 Vulcan cannon in the left wing root and has 11 hardpoints for mounting various missiles, bombs and pods. It was also the first fighter aircraft purpose built to sustain 9-g turns. It has a thrust-to-weight ratio greater than one, providing power to climb and accelerate vertically.

Early models could be armed with up to six AIM-9 Sidewinder heat-seeking short-range air-to-air missiles (AAM), including rail launchers on each wingtip. Some F-16s can employ the AIM-7 Sparrow medium-range AAM; more recent versions can equip the AIM-120 AMRAAM. It can also carry other AAM; a wide variety of air-to-ground missiles, rockets or bombs; electronic countermeasures (ECM), navigation, targeting or weapons pods; and fuel tanks on 11 hardpoints – six under the wings, two on wingtips and three under the fuselage.

General configuration

The F-16 has a cropped-delta planform incorporating wing-fuselage blending and forebody vortex-control strakes; a fixed-geometry, underslung air intake to the single turbofan jet engine; a conventional tri-plane empennage arrangement with all-moving horizontal "stabilator" tailplanes; a pair of ventral fins beneath the fuselage aft of the wing's trailing edge; a single-piece, bird-proof "bubble" canopy; and a tricycle landing gear configuration with the aft-retracting, steerable nose gear deploying a short distance behind the inlet lip. There is a boom-style aerial refueling receptacle located a short distance behind the canopy. Split-flap speedbrakes are located at the aft end of the wing-body fairing, and an arrestor hook is mounted underneath the fuselage. Another fairing is situated beneath the bottom of the rudder, often used to house ECM equipment or a drag chute. Several later F-16 models, such as the F-16I, also have a long dorsal fairing "bulge" along the "spine" of the fuselage from the cockpit's rear to the tail fairing, it can be used for additional equipment or fuel.

The F-16 was designed to be relatively inexpensive to build and simpler to maintain than earlier-generation fighters. The airframe is built with about 80% aviation-grade aluminum alloys, 8% steel, 3% composites, and 1.5% titanium. The leading-edge flaps, tailerons, and ventral fins make use of bonded aluminum honeycomb structures and graphite epoxy laminate coatings. The number of lubrication points, fuel line connections, and replaceable modules is significantly lower than predecessors; 80% of access panels can be accessed without stands. The air intake was designed: "far enough forward to allow a gradual bend in the air duct up to the engine face to minimize flow losses and far enough aft so it wouldn't weigh too much or be too draggy or destabilizing."

Although the LWF program called for an aircraft structural life of 4,000 flight hours, capable of achieving 7.33 g with 80% internal fuel; GD's engineers decided to design the F-16's airframe life for 8,000 hours and for 9-g maneuvers on full internal fuel. This proved advantageous when the aircraft's mission changed from solely air-to-air combat to multi-role operations. Since introduction, changes in operational usage and additional systems have increased aircraft weight, necessitating several programs to strengthen its structure.

Wing and strake configuration

Aerodynamic studies in the early 1960s demonstrated that the phenomenon known as "vortex lift" could be beneficially harnessed by the adoption of highly swept wing configurations to reach higher angles of attack through use of the strong leading edge vortex flow off a slender lifting surface. Since the F-16 was being optimized for high agility in air combat, GD's designers chose a slender cropped-delta wing with a leading edge sweep of 40° and a straight trailing edge. To improve maneuverability, a variable-camber wing with a NACA 64A-204 airfoil was selected; the camber is adjusted by leading-edge and trailing edge flaperons linked to a digital flight control system (FCS) regulating the flight envelope. The F-16 has a moderate wing loading, which is lower when fuselage lift is considered.

The vortex lift effect is increased by extensions of the leading edge at the wing root (the juncture with the fuselage) known as a strake. Strakes act as an additional elongated, short-span, triangular wing running from the actual wing root to a point further forward on the fuselage. Blended into the fuselage and along the wing root, the strake generates a high-speed vortex that remains attached to the top of the wing as the angle of attack increases, thereby generating additional lift and thus allowing greater angles of attack without stalling. The use of strakes also allows a smaller, lower-aspect-ratio wing, which increases roll rates and directional stability while decreasing weight. Deeper wingroots also increase structural strength and increase internal fuel volume.

Negative stability and Fly-by-wire

The F-16 was the first production fighter aircraft intentionally designed to be slightly aerodynamically unstable, also known as "relaxed static stability" (RSS), to improve maneuverability.[46] Most aircraft are designed with positive static stability, which induces aircraft to return to straight and level flight attitude if the pilot releases the controls. This reduces maneuverability as the aircraft must overcome its inherent stability in order to maneuver. Aircraft with negative stability are designed to deviate from controlled flight and thus be more maneuverable. At supersonic speeds the F-16 gains stability (eventually positive) due to changes in aerodynamic forces.

To counter the tendency to depart from controlled flight—and avoid the need for constant trim inputs by the pilot, the F-16 has a quadruplex (four-channel) fly-by-wire (FBW) flight control system (FLCS). The flight control computer (FLCC) accepts pilot input from the stick and rudder controls, and manipulates the control surfaces in such a way as to produce the desired result without inducing control loss. The FLCC conducts thousands of measurements per second on the aircraft's flight attitude to automatically counter deviations from the pilot-set flight path; leading to a common aphorism among pilots: "You don't fly an F-16; it flies you."

The FLCC further incorporates limiters that govern movement in the three main axes based on current attitude, airspeed and angle of attack (AOA), and prevent control surfaces from inducing instability such as slips or skids, or a high AOA inducing a stall. The limiters also prevent maneuvers that would exert more than a 9 g load. Although each axis of movement is limited by the FLCC, flight testing revealed that "assaulting" multiple limiters at high AOA and low speed can result in an AOA far exceeding the 25° limit; colloquially referred to as "departing". This cause a deep stall; a near-freefall at 50° to 60° AOA, either upright or inverted. While at a very high AOA, the aircraft's attitude is stable but control surfaces are ineffective and the aircraft's pitch limiter locks the stabilators at an extreme pitch-up or pitch-down attempting to recover; the pitch-limiting can be overridden so the pilot can "rock" the nose via pitch control to recover.

Unlike the YF-17, which had hydromechanical controls serving as a backup to the FBW, Grumman took the innovative step of eliminating mechanical linkages between the stick and rudder pedals and the aerodynamic control surfaces. The F-16 is entirely reliant on its electrical systems to relay flight commands, instead of traditional mechanically-linked controls, leading to the early moniker of "the electric jet". The quadruplex design permits "graceful degradation" in flight control response in that the loss of one channel renders the FLCS a "triplex" system. The FLCC began as an analog system on the A/B variants, but has been supplanted by a digital computer system beginning with the F-16C/D Block 40. The F-16's controls suffered from a sensitivity to static electricity or electrostatic discharge (ESD). Up to 70–80% of the C/D models' electronics were vulnerable to ESD.

Cockpit and ergonomics

One feature of the F-16 for air-to-air combat performance is the cockpit's exceptional field of view. The single-piece, bird-proof polycarbonate bubble canopy provides 360° all-round visibility, with a 40° look-down angle over the side of the aircraft, and 15° down over the nose (compared to the more common 12–13° of preceding aircraft); the pilot's seat is elevated for this purpose. Furthermore, the F-16's canopy lacks the forward bow frame found on many fighters, which is an obstruction to a pilot's forward vision.

The F-16's ACES II zero/zero ejection seat is reclined at an unusual tilt-back angle of 30°; most fighters have a tilted seat at 13–15°. The seat angle was chosen to improve pilot tolerance of high g forces and reduce susceptibility to gravity-induced loss of consciousness. The seat angle has been associated with reports of neck ache, possibly caused by incorrect use of the head-rest. Subsequent U.S. fighters have adopted more modest tilt-back angles of 20°. Due to the seat angle and the canopy's thickness, the F-16's ejection seat lacks steel canopy breakers for emergency egress; instead the entire canopy is jettisoned prior to the seat's rocket firing.

The pilot flies primarily by means of an armrest-mounted side-stick controller (instead of a traditional center-mounted stick) and an engine throttle; conventional rudder pedals are also employed. To enhance the pilot's degree of control of the aircraft during high-g combat maneuvers, various switches and function controls were moved to centralised "hands on throttle-and-stick (HOTAS)" controls upon both the controllers and the throttle. Hand pressure on the side-stick controller is transmitted by electrical signals via the FBW system to adjust various flight control surfaces to maneuver the F-16. Originally the side-stick controller was non-moving, but this proved uncomfortable and difficult for pilots to adjust to, sometimes resulting in a tendency to "over-rotate" during takeoffs, so the control stick was given a small amount of "play". Since introduction on the F-16, HOTAS controls have become a standard feature on modern fighters.

The F-16 has a head-up display (HUD), which projects visual flight and combat information in front of the pilot without obstructing the view; being able to keep his head "out of the cockpit" improves a pilot's situational awareness. Further flight and systems information are displayed on multi-function displays (MFD). The left-hand MFD is the primary flight display (PFD), typically showing radar and moving-maps; the right-hand MFD is the system display (SD), presenting information about the engine, landing gear, slat and flap settings, and fuel and weapons status. Initially, the F-16A/B had monochrome cathode ray tube (CRT) displays; replaced by color liquid crystal displays on the Block 50/52. The MLU introduced compatibility with night-vision goggles (NVG). The Boeing Joint Helmet Mounted Cueing System (JHMCS) is available from Block 40 onwards, for targeting based on where the pilot's head faces, unrestricted by the HUD, using high-off-boresight missiles like the AIM-9X.

Fire-control radar

The F-16A/B was originally equipped with the Westinghouse AN/APG-66 fire-control radar. Its slotted planar-array antenna was designed to be compact to fit into the F-16's relatively small nose. In uplook mode, the APG-66 uses a low pulse-repetition frequency (PRF) for medium- and high-altitude target detection in a low-clutter environment, and in downlook employs a medium PRF for heavy clutter environments. It has four operating frequencies within the X band, and provides four air-to-air and seven air-to-ground operating modes for combat, even at night or in bad weather. The Block 15's APG-66(V)2 model added a more powerful signal processor, higher output power, improved reliability and increased range in cluttered or jamming environments. The Mid-Life Update (MLU) program introduced a new model, APG-66(V)2A, which features higher speed and more memory.

The AN/APG-68, an evolution of the APG-66, was introduced with the F-16C/D Block 25. The APG-68 has greater range and resolution, as well as 25 operating modes, including ground-mapping, Doppler beam-sharpening, ground moving target, sea target, and track-while-scan (TWS) for up to 10 targets. The Block 40/42's APG-68(V)1 model added full compatibility with Lockheed Martin Low-Altitude Navigation and Targeting Infra-Red for Night (LANTIRN) pods, and a high-PRF pulse-Doppler track mode to provide continuous-wave (CW) target illumination for semi-active radar-homing (SARH) missiles like the AIM-7 Sparrow. Block 50/52 F-16s initially used the more reliable APG-68(V)5 which has a programmable signal processor employing Very-High-Speed Integrated Circuit (VHSIC) technology. The Advanced Block 50/52 (or 50+/52+) are equipped with the APG-68(V)9 radar, with a 30% greater air-to-air detection range and a synthetic aperture radar (SAR) mode for high-resolution mapping and target detection-recognition. In August 2004, Northrop Grumman were contracted to upgrade the APG-68 radars of the Block 40/42/50/52 aircraft to the (V)10 standard, providing the F-16 with all-weather autonomous detection and targeting for Global Positioning System (GPS)-aided precision weapons. It also adds SAR mapping and terrain-following (TF) modes, as well as interleaving of all modes.

The F-16E/F is outfitted with Northrop Grumman's AN/APG-80 Active Electronically Scanned Array (AESA) radar, making it only the third fighter to be so equipped. Northrop Grumman is continuing development upon this latest radar, to form the Scalable Agile Beam Radar (SABR). In July 2007, Raytheon announced that it was developing a Next Generation Radar (RANGR) based on its earlier AN/APG-79 AESA radar as a competitor to Northrop Grumman's AN/APG-68 and AN/APG-80 for the F-16.

Propulsion

The powerplant first selected for the single-engined F-16 was the Pratt & Whitney F100-PW-200 afterburning turbofan, a slightly modified version of the F100-PW-100 used by the F-15. Rated at 23,830 lbf (106.0 kN) thrust, it was the standard F-16 engine through the Block 25, except for new-build Block 15s with the Operational Capability Upgrade (OCU). The OCU introduced the 23,770 lbf (105.7 kN) F100-PW-220, which was also installed on Block 32 and 42 aircraft: the main advance being a Digital Electronic Engine Control (DEEC) unit, which improved engine reliability and reduced stall occurrence. Added to the production line in 1988 the "-220" also supplanted the F-15's "-100", for commonality. Many of the "-220" engines on Block 25 and later aircraft were upgraded from mid-1997 to the "-220E" standard, which enhanced reliability and engine maintainability, unscheduled engine removals were reduced by 35%.

The F100-PW-220/220E was the result of the USAF's Alternate Fighter Engine (AFE) program (colloquially known as "the Great Engine War"), which also saw the entry of General Electric as an F-16 engine provider. Its F110-GE-100 turbofan was limited by the original inlet to thrust of 25,735 lbf (114.5 kN), the Modular Common Inlet Duct allowed the F110 to achieve its maximum thrust of 28,984 lbf (128.9 kN). (To distinguish between aircraft equipped with these two engines and inlets, from the Block 30 series on, blocks ending in "0" (e.g., Block 30) are powered by GE, and blocks ending in "2" (e.g., Block 32) are fitted with Pratt & Whitney engines.

The Increased Performance Engine (IPE) program led to the 29,588 lbf (131.6 kN) F110-GE-129 on the Block 50 and 29,160 lbf (129.4 kN) F100-PW-229 on the Block 52. F-16s began flying with these IPE engines in the early 1990s. Altogether, of the 1,446 F-16C/Ds ordered by the USAF, 556 were fitted with F100-series engines and 890 with F110s. The United Arab Emirates’ Block 60 is powered by the General Electric F110-GE-132 turbofan, which is rated at a maximum thrust of 32,500 lbf (144.6 kN), the highest developed for the F-16.

The Lockheed Martin F-35 Lightning II

F-35 or The Lockheed Martin F-35 Lightning II, is a family of single-seat, single-engine, fifth generation multirole fighters under development to perform ground attack, reconnaissance, and air defense missions with stealth capability. The F-35 has three main models, they are: the conventional takeoff and landing variant, the second is a short take off and vertical-landing variant, and the third is a carrier-based variant. The F-35 is descended from the X-35, the product of the Joint Strike Fighter (JSF) program. JSF development is being principally funded by the United States, with the United Kingdom and other partner governments providing additional funding. The partner nations are either NATO members or close U.S. allies. It is being designed and built by an aerospace industry team led by Lockheed Martin. The F-35 took its first flight on 15 December 2006.

The F-35 appears to be a smaller, slightly more conventional, single-engine sibling of the sleeker, twin-engine Lockheed Martin F-22 Raptor, and indeed drew elements from it. The exhaust duct design was inspired by the General Dynamics Model 200 design, which was proposed for a 1972 supersonic VTOL fighter requirement for the Sea Control Ship. For specialized development of the F-35B STOVL variant, Lockheed consulted with the Yakovlev Design Bureau, purchasing design data from their development of the Yakovlev Yak-141 "Freestyle". Although several experimental designs have been built and tested since the 1960s including the Navy's unsuccessful Rockwell XFV-12, the F-35B is to be the first operational supersonic, STOVL stealth fighter. The F-35 has a maximum speed of over Mach 1.6. With a maximum takeoff weight of 60,000 lb (27,000 kg), the Lightning II is considerably heavier than the lightweight fighters it replaces. In empty and maximum gross weights, it more closely resembles the single-seat, single-engine Republic F-105 Thunderchief, which was the largest single-engine fighter of the Vietnam war era. However the F-35's modern engine delivers over 60 percent more thrust in an aircraft of the same weight so that in thrust to weight and wing loading it is much closer to a comparably equipped F-16.

The F-35's main engine is the Pratt & Whitney F135. The General Electric/Rolls-Royce F136 was under development as an alternative engine until December 2011 when the manufacturers canceled work on it. The F135/F136 engines are not designed to supercruise in the F-35. The STOVL versions of both power plants use the Rolls-Royce LiftSystem, patented by Lockheed Martin and developed and built by Rolls-Royce. This system is more like the Russian Yak-141 and German VJ 101D/E than the preceding generation of STOVL designs, such as the Harrier Jump Jet in which all of the lifting air went through the main fan of the Rolls-Royce Pegasus engine. The Lift System is composed of a lift fan, drive shaft, two roll posts and a "Three Bearing Swivel Module" (3BSM). The 3BSM is a thrust vectoring nozzle which allows the main engine exhaust to be deflected downward at the tail of the aircraft. The lift fan is near the front of the aircraft and provides a counter-balancing thrust using two counter-rotating blisks. It is powered by the engine's low-pressure (LP) turbine via a drive shaft and gearbox. Roll control during slow flight is achieved by diverting unheated engine bypass air through wing mounted thrust nozzles called Roll Posts. Like lift engines, the added lift fan machinery increases payload capacity during vertical flight, but is dead weight during horizontal flight. The cool exhaust of the fan also reduces the amount of hot, high-velocity air that is projected downward during vertical take off, which can damage runways and aircraft carrier decks. To date, F136 funding has come at the expense of other parts of the program, reducing the number of aircraft built and increasing their costs. The F136 team has claimed that their engine has a greater temperature margin which may prove critical for VTOL operations in hot, high altitude conditions. Pratt & Whitney is also testing higher thrust versions of the F135, partly in response to GE's claims that the F136 is capable of producing more thrust than the 43,000 lbf (190 kN) supplied by early F135s. The F135 has demonstrated a maximum thrust of over 50,000 lbf (220 kN) during testing. The F-35's Pratt & Whitney F135 is the most powerful engine ever installed in a fighter aircraft. The F135 is the second (radar) stealthy afterburning jet engine and like the Pratt & Whitney F119 from which it was derived, has suffered from pressure pulsations in the afterburner at low altitude and high speed or "screech". In both cases this problem was fixed during development of the fighter program. Turbine bearing health in the engine will be monitored with thermoelectric powered wireless sensors.

Eurofighter Typhoon

The Eurofighter Typhoon is a twin-engine, canard-delta wing, multirole combat aircraft, designed and built by a consortium of three companies: EADS, Alenia Aeronautica and BAE Systems; working through a holding company, Eurofighter GmbH, which was formed in 1986. The project is managed by the NATO Eurofighter and Tornando Management Agency, which acts as the prime customer. The series production of the Eurofighter Typhoon is underway, and the aircraft is being procured under separate contracts, named "tranches", each for aircraft with generally improved capabilities. The aircraft has entered service with the Austrian Air Force, the Italian Air Force, the German Luftwaff, the British Royal Air Force, the Spanish Air Force, and the Royal Saudi Air Force.

Origins

The UK had identified a requirement for a new fighter as early as 1971. A specification, AST 403, issued by the Air Staff in 1972, resulted in a conventional "tailed" design known as P.96, which was presented in the late 1970s. While the design would have met the Air Staff's requirements, the UK air industry had reservations as it appeared to be very similar to the McDonnell Douglas F/A-18 Hornet, which was then well advanced in its development. The design had little potential for future growth, and when it entered production it would secure few exports in a market in which the Hornet would be well established. However, the simultaneous West German requirement for a new fighter had led by 1979 to the development of the TKF-90 concept. This was a cranked delta wing design with forward canard controls and artificial stability. Although the British Aerospace designers rejected some of its advanced features such as vectoring engine nozzles and vented trailing-edge controls, they agreed with the overall configuration.

In 1979,Messerschmitt-bolkow-blohm (MBB) and British Aerospace (BAe) presented a formal proposal to their respective governments for the ECF, the European Collaborative Fighteror European Combat Fighter. In October 1979 Dassault joined the ECF team for a tri-national study, which became known as the European Combat Aircraft. It was at this stage of development that the Eurofighter name was first attached to the aircraft. The development of different national prototypes continued. France produced the ACX. The UK produced two designs; the P.106was a single-engined "lightweight" fighter, superficially resembling the JAS 39 Gripen, the P.110 was a twin-engined fighter. The P.106 concept was rejected by the RAF, on the grounds that it had "half the effectiveness of the two-engined aircraft at two thirds of the cost". West Germany continued to refine the TFK-90 concept. The ECA project collapsed in 1981 for several reasons including differing requirements, Dassault's insistence on "design leadership" and the British preference for a new version of the RB 199 to power the aircraft versus the French preference for the new Snecma M88.

As a result the Panavia partners (MBB, BAe and Aeritalia) launched the Agile Combat Aircraft (ACA) programme in April 1982. The ACA was very similar to the BAe P.110, having a cranked delta wing, canards and a twin tail. One major external difference was the replacement of the side mounted engine intakes with a chin intake. The ACA was to be powered by a modified version of the RB199. The German and Italian governments withdrew funding, and the UK Ministry of Defence agreed to fund 50% of the cost with the remaining 50% to be provided by industry. MBB and Aeritalia signed up with the aim of producing two aircraft, one at Warton and one by MBB. In May 1983 BAe announced a contract with the Mod for the development and production of an ACA demonstrator, the Experimental Aircraft Programme.

In 1983 the Germany, France, UK, Italy and Spain launched the Future European Fighter Aircraft (FEFA) programme. The aircraft was to have short take off and landing (STOL) and beyond visual range (BVR) capabilities. In 1984 France reiterated its requirement for a carrier-capable version and demanded a leading role. The West Germany, UK and Italy opted out and established a new EFA programme. In Turin on 2 August 1985, West Germany, UK and Italy agreed to go ahead with the Eurofighter; and confirmed that France, along with Spain, had chosen not to proceed as a member of the project. Despite pressure from France, Spain rejoined the Eurofighter project in early September 1985. France officially withdrew from the project to pursue its own ACX project, which was to become the Dassault Rafale. By 1986, the cost of the programme had reached £180 million. When the EAP programme had started, the cost was supposed to be equally shared by both government and industry, but the West German and Italian government wavered on the agreement and the three main industrial partners had to provide £100 million to keep the programme from ending. In April 1986 the BAe EAP was rolled out at BAe Warton, by this time also partially funded by MBB, BAe and Aeritalia. The EAP first flew on 6 August 1986. The Eurofighter bears a strong resemblance to the EAP. Design work continued over the next five years using data from the EAP. Initial requirements were: UK: 250 aircraft, Germany: 250, Italy: 165 and Spain: 100. The share of the production work was divided among the countries in proportion to their projected procurement – DASA (33%),British Aerospace (33%),Aeritalia (21%), and Construcciones Aeronauticas SA (CASA) (13%).

The Munich based Eurofighter Jagdflugzeug GmbH was established in 1986 to manage development of the project and EuroJet Turbo GmbH, the alliance of Rolls-Royce, MTU Aero Engines, FiatAvio (now Avio) and ITP for development of the EJ200. The aircraft was known as Eurofighter EFA from the late 1980s until it was renamed EF 2000 in 1992. By 1990, the selection of the aircraft's radar had become a major stumbling block. The UK, Italy and Spain supported the Ferranti Defence Systems -led ECR-90, while Germany preferred the APG-65 based MSD2000 (a collaboration between Hughes, AEG and GEC-Marconi). An agreement was reached after UK Defence Secretary Tom King assured his West German counterpart Gerhard Stoltenberg that the British government would approve the project and allow GEC to acquire Ferranti Defence Systems from its troubled parent. GEC thus withdrew its support for the MSD2000.

Testing

The maiden flight of the Eurofighter prototype took place in Bavaria on 27 March 1994, flown by DASA Chief Test Pilot Peter Weger. On 9 December 2004, Eurofighter Typhoon IPA4 began three months of Cold Environmental Trials (CET) at the Vidsel Air Base in Sweden, the purpose of which was to verify the operational behaviour of the aircraft and its systems in temperatures between −25 and 31 °C. The maiden flight of Instrumented Production Aircraft 7 (IPA7), the first fully equipped Tranche 2 aircraft, took place from EADS' Manching airfield on 16 January 2008.

In May 2007, Eurofighter Development Aircraft 5 made the first flight with the CAESAR demonstrator system, a development of the Euroradar CAPTOR incorporating Active Electronically Scanned Array (AESA) technology. The production version of the CAPTOR-E radar was being proposed as part of Tranche 3 of the Typhoon from 2012. Tranche 2 aircraft use the non AESA, mechanically scanned Captor-M which incorporates weight and space provisions for possible upgrade to CAESAR (AESA) standard in the future. The Italian Air Force doubted that the AESA radar would be ready in time for Tranche 3 production. In July 2010, Eurofighter announced that the AESA radar would enter service in 2015.

Costs

In 1988, the Parliamentary Under-Secretary of State for the Armed Forces told the UK House of Commons that the European Fighter Aircraft would "be a major project, costing the United Kingdom about £7 billion". It was soon apparent that a more realistic estimate was £13 billion, made up of £3.3 billion development costs plus £30 million per aircraft. By 1997 the estimated cost was £17 billion; by 2003, £20 billion, and the in-service date (2003; defined as the date of delivery of the first aircraft to the RAF) was 54 months late. After 2003 the Ministry of Defence have refused to release updated cost estimates on the grounds of 'commercial sensitivity', however in 2011 the National Audit Office estimated the UK's "total programme cost eventually hit £37 billion".

By 2007, Germany estimated the system cost (aircraft, training plus spare parts) to €120m and said it was in perpetual increase. On 17 June 2009, Germany ordered 31 aircraft of Tranche 3A for €2,800m, leading to a system cost of €90m per aircraft. The UK’s Committee of Public Accounts reported that the mismanagement of the project had helped increase the cost of each aircraft by 75 percent. Defence Secretary Lian Fox responded that "I am determined that in the future such projects are properly run from the outset, and I have announced reforms to reduce equipment delays and cost overruns."

Delays

The financial burdens placed on Germany by reunification caused Helmut Kohl to make an election promise to cancel the Eurofighter. In early to mid-1991 German Defence Minister Volker Ruhe sought to withdraw Germany from the project in favour of using Eurofighter technology in a cheaper, lighter plane. Due to the amount of money already spent on development, the number of jobs dependent on the project, and the binding commitments on each partner government, Helmut Kohl was unable to withdraw; "Rühe's predecessors had locked themselves into the project by a punitive penalty system of their own devising."

In 1995 concerns over workshare appeared. Since the formation of Eurofighter the workshare split had been agreed at the 33/33/21/13 (United Kingdom/Germany/Italy/Spain) based on the number of units being ordered by each contributing nation. All the nations then reduced their orders. The UK cut its orders from 250 to 232, Germany from 250 to 140, Italy from 165 to 121 and Spain from 100 to 87. According to these order levels the workshare split should have been 39/24/22/15 UK/Germany/Italy/Spain, Germany was unwilling to give up such a large amount of work. In January 1996, after much negotiation between German and UK partners, a compromise was reached whereby Germany would purchase another 40 aircraft. The workshare split is now 43% for EADS MAS in Germany and Spain; 37.5% BAE Systems in the UK; and 19.5% for Alenia in Italy.

The next major milestone came at the Farnborough Airshow in September 1996. The UK announced the funding for the construction phase of the project. In November 1996 Spain confirmed its order but Germany delayed its decision. After much diplomatic activity between Germany and UK, an interim funding arrangement of DM 100 million (€51 million) was contributed by the German government in July 1997 to continue flight trials. Further negotiation finally resulted in German approval to purchase the Eurofighter in October 1997.