.: Jamie McDonald's 1/72nd "RAAF" what-if Warthogs

Brand:
Academy/Hobby Boss
Scale:
1/72nd
Modelling Time:
~10 hrs each
PE/Resin Detail:
none
Comments:
Straight Out of the Box, more "What-Ifs" from Jamie...

Fairchild Republic A-10 Thunderbolt II

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"A-10" redirects here. For other uses, see A10.
A-10 Thunderbolt II
Role Fixed-wing close air support, forward air control, and ground-attack aircraft
Manufacturer Fairchild Republic
First flight 10 May 1972
Introduction March 1977
Status In service
Primary user United States Air Force
Produced 1972–1984
Number built 716[1]
Unit cost US$11.8 million (average, 1994 dollars)[2]

The Fairchild Republic A-10 Thunderbolt II is an American single-seat, twin-engine, straight-wing jet aircraft developed by Fairchild-Republic in the early 1970s. The A-10 was designed for a United States Air Force (USAF) requirement to provide close air support (CAS) for ground forces by attacking tanks and other armored vehicles, and other ground targets with a limited air defense capability. It was the first USAF aircraft designed solely for CAS.

The A-10 was designed around the GAU-8 Avenger, a heavy rotary cannon that forms the aircraft's primary armament. (It is, to date, the heaviest rotary cannon ever mounted on an aircraft.) The aircraft's hull incorporates over 1,200 pounds (540 kg) of armor and was designed with survivability as a priority, with protective measures in place which enable the aircraft to continue flying even after taking significant damage.

The A-10's official name comes from the Republic P-47 Thunderbolt of World War II, a fighter that was particularly effective at close air support. The A-10 is more commonly known by its nickname "Warthog" or simply "Hog". As a secondary mission, it provides airborne forward air control, guiding other aircraft against ground targets. A-10s used primarily in this role are designated OA-10. The A-10 is not expected to be replaced until 2028 or later.

Development

Background

Criticism that the U.S. Air Force did not take close air support (CAS) seriously prompted a few service members to seek a specialized attack aircraft.[3][4] In the Vietnam War, large numbers of ground-attack aircraft were shot down by small arms, surface-to-air missiles, and low-level anti-aircraft gunfire, prompting the development of an aircraft better able to survive such weapons. In addition, the UH-1 Iroquois and AH-1 Cobra helicopters of the day, which USAF commanders had said should handle close air support, were ill-suited for use against armor, carrying only anti-personnel machine guns and unguided rockets meant for soft targets. Fast jets such as the F-100 Super Sabre, F-105 Thunderchief and F-4 Phantom II proved for the most part to be ineffective for close air support, because their high speed did not allow pilots enough time to get an accurate fix on ground targets and they lacked sufficient loiter time. The effective, but aging A-1 Skyraider was the USAF's primary close air support aircraft.[5][6]

A-X program

In 1966 the USAF formed the Attack Experimental (A-X) program office.[7] On 6 March 1967, the Air Force released a request for information to 21 defense contractors for the A-X. The objective was to create a design study for a low-cost attack aircraft.[4] In 1969, the Secretary of the Air Force asked Pierre Sprey to write the detailed specifications for the proposed A-X project. However, his initial involvement was kept secret because of Sprey's earlier controversial involvement in the F-X project.[4]

Sprey's discussions with A-1 Skyraider pilots operating in Vietnam and analysis of the effectiveness of current aircraft used in the role indicated the ideal aircraft should have long loiter time, low-speed maneuverability, massive cannon firepower, and extreme survivability;[4] an aircraft that had the best elements of the Ilyushin Il-2, Henschel Hs 129 and Skyraider. The specifications also demanded that each aircraft cost less than $3 million.[4] Sprey required that the biography of World War II attack pilot Hans-Ulrich Rudel be read by people on A-X program.[8]

In May 1970, the USAF issued a modified and much more detailed request for proposals (RFP) for the aircraft. The threat of Soviet armored forces and all-weather attack operations had become more serious. Now included in the requirements was that the aircraft would be designed specifically for the 30 mm cannon. The RFP also specified an aircraft with a maximum speed of 460 mph (400 kn; 740 km/h), takeoff distance of 4,000 feet (1,200 m), external load of 16,000 pounds (7,300 kg), 285-mile (460 km) mission radius, and a unit cost of US$1.4 million.[9] The A-X would be the first Air Force aircraft designed exclusively for close air support.[10]

During this time, a separate RFP was released for A-X's 30 mm cannon with requirements for a high rate of fire (4,000 round/minute) and a high muzzle velocity.[11] Six companies submitted aircraft proposals to the USAF, with Northrop and Fairchild Republic selected to build prototypes: the YA-9A and YA-10A, respectively. General Electric and Philco-Ford were selected to build and test GAU-8 cannon prototypes.[12]

The YA-10A was built in Hagerstown, Maryland and first flew on 10 May 1972. After trials and a fly-off against the YA-9A, the Air Force announced its selection of Fairchild-Republic's YA-10A on 18 January 1973 for production.[13] General Electric was selected to build the GAU-8 cannon in June 1973.[14] The YA-10 had an additional fly-off in 1974 against the Ling-Temco-Vought A-7D Corsair II, the principal Air Force attack aircraft at the time, in order to prove the need to purchase a new attack aircraft. The first production A-10 flew in October 1975, and deliveries to the Air Force commenced in March 1976. In total, 715 airplanes were produced, the last delivered in 1984.[15]

One experimental two-seat A-10 Night Adverse Weather (N/AW) version was built by converting an A-10A.[16] The N/AW was developed by Fairchild from the first Demonstration Testing and Evaluation (DT&E) A-10 for consideration by the USAF. It included a second seat for a weapons system officer responsible for electronic countermeasures (ECM), navigation and target acquisition. The variant was canceled, and the only two-seat A-10 built now resides at Edwards Air Force Base's Flight Test Center Museum.[17] The N/AW version did not interest the USAF or export customers. The two-seat trainer version was ordered by the Air Force in 1981, but funding was canceled by U.S. Congress and the jet was not produced.[18]

Upgrades

The A-10 has received many upgrades over the years. Aircraft added the Pave Penny laser receiver pod beginning in 1978. It senses reflected laser radiation from a laser designator on a target for faster and more accurate target identification.[19][20][21] The A-10 began receiving an inertial navigation system in 1980.[22] Later, the Low-Altitude Safety and Targeting Enhancement (LASTE) upgrade provided computerized weapon-aiming equipment, an autopilot, and a ground-collision warning system. The A-10 is now compatible with night vision goggles for low-light operation. In 1999, aircraft began to receive Global Positioning System navigation systems and a new multi-function display.[23] Its LASTE system is being upgraded with the Integrated Flight & Fire Control Computers (IFFCC).[24]

In 2005, the entire A-10 fleet also began receiving the Precision Engagement upgrades that include an improved fire control system (FCS), electronic countermeasures (ECM), and the ability to aim smart bombs. The aircraft that receive this upgrade are redesignated A-10C. The A-10 will receive a service life extension program (SLEP) upgrade with many receiving new wings.[25] A contract to build 242 new A-10 wing sets was awarded to Boeing in June 2007.[26] In July 2010, the USAF issued Raytheon a contract to integrate a Helmet Mounted Integrated Targeting (HMIT) system into A-10Cs.[27] Two A-10s flew in November 2011 with the new wing installed. The service life of the re-winged aircraft is extended to 2040.

The Government Accounting Office in 2007 estimated the cost of upgrading, refurbishing, and service life extension plans for the A-10 force to total $2.25 billion through 2013.[10] Modifications to provide precision weapons capability are well underway.[27] The Air Force Material Command's Ogden Air Logistics Center at Hill AFB, Utah completed work on its 100th A-10 precision engagement upgrade in January 2008.[28] The C model upgrades are to be completed in 2011.[29]

Design

Overview

The A-10 has superior maneuverability at low speeds and altitude because of its large wing area, high wing aspect ratio, and large ailerons. The high aspect ratio wing also allows for short takeoffs and landings, permitting operations from primitive forward airfields near front lines. The aircraft can loiter for extended periods and operate under 1,000 ft (300 m) ceilings with 1.5 mi (2.4 km) visibility. It typically flies at a relatively slow speed of 300 knots (350 mph; 560 km/h), which makes it a much better platform for the ground-attack role than fast fighter-bombers, which often have difficulty targeting small and slow-moving targets.[5]

Engine exhaust passes over the aircraft's horizontal stabilizer and between the twin tails, decreasing the A-10's infrared signature and lowering the likelihood that the aircraft can be targeted by heat-seeking missiles fired from the ground. The placement of the engines behind the wings partially shields them from anti-aircraft fire.[30] The leading edge of the wing is honeycomb panel construction to provide strength with minimal weight compromise. Honeycomb panels of this type on the A-10 include the flap shrouds, elevators, rudders and other sections of the fins.[31]

The A-10 has integrally machined skin panels. Because the stringers are integral with the skin there are no joint or seal problems. These panels, fabricated using computer controlled machining, reduce the time and hence the cost of production. Combat experience has shown that this type of panel is more resistant to damage. The skin is not load-bearing, so damaged skin sections can be easily replaced in the field, with makeshift materials if necessary.[32]

The ailerons are at the far ends of the wings to gain greater rolling moment, as with many aircraft, but there are two distinguishing features. The ailerons are larger than is typical, almost 50% of the wingspan, providing improved control even at slow speeds. The aileron is also split, making it a deceleron.[33][34]

The A-10 is designed to be refueled, rearmed, and serviced with minimal equipment.[35] Also, most repairs can be done in the field.[36] An unusual feature is that many of the aircraft's parts are interchangeable between the left and right sides, including the engines, main landing gear, and vertical stabilizers. The sturdy landing gear, low-pressure tires and large, straight wings allow operation from short rough strips even with a heavy ordnance load, allowing the aircraft to operate from damaged airbases. If runways are damaged in an attack, the A-10 can operate from taxiways or straight roadway sections.[37]

The front landing gear is offset to the aircraft's right to allow placement of the 30 mm cannon with its firing barrel along the centerline of the aircraft.[38] During ground taxi, the offset front landing gear causes the A-10 to have dissimilar turning radii. Turning to the right on the ground takes less distance than turning left.[Note 1]

Durability

The A-10 is exceptionally tough. Its strong airframe can survive direct hits from armor-piercing and high-explosive projectiles up to 23 mm. The aircraft has triple redundancy in its flight systems, with mechanical systems to back up double-redundant hydraulic systems. This permits pilots to fly and land when hydraulic power or part of a wing is lost. Flight without hydraulic power uses the manual reversion flight control system; this engages automatically for pitch and yaw control, and under pilot control (manual reversion switch) for roll control. In manual reversion mode, the A-10 is sufficiently controllable under favorable conditions to return to base and land, though control forces are much higher than normal. The aircraft is designed to fly with one engine, one tail, one elevator, and half of one wing missing.[39]

Its self-sealing fuel tanks are protected by fire-retardant foam.[40] The A-10's main landing gear is designed so that the wheels partially protrude from their nacelles when the gear is retracted so as to make gear-up belly landings easier to control and less damaging to the aircraft's underside. Additionally, the landing gear are all hinged toward the rear of the aircraft, so if hydraulic power is lost the pilot can drop the gear and a combination of gravity and wind resistance will open and lock the gear in place.[34]

The cockpit and parts of the flight-control system are protected by 1,200 lb (540 kg) of titanium armor, referred to as a "bathtub".[41][42] The armor has been tested to withstand strikes from 23 mm cannon fire and some strikes from 57 mm rounds.[36][41] It is made up of titanium plates with thicknesses from 0.5 to 1.5 inches (13 to 38 mm) determined by a study of likely trajectories and deflection angles. This protection comes at a cost, with the armor making up almost 6% of the aircraft's empty weight. To protect the pilot from the fragmentation likely to be created from impact of a shell, any interior surface of the tub that is directly exposed to the pilot is covered by a multi-layer nylon spall shield.[40][43] In addition, the front windscreen and canopy are resistant to small arms fire.[44]

Proof of the durability of the A-10 was shown when Captain Kim Campbell, flying a ground support mission over Baghdad during the 2003 invasion of Iraq on 7 April, suffered extensive flak damage to her A-10. Iraqi fire damaged one of the A-10's engines and crippled its hydraulic system, which required the aircraft's stabilizer and flight controls to be operated via the back-up mechanical system, this being known as 'manual reversion mode'. Despite this damage, Campbell managed to fly the aircraft for nearly an hour and landed safely.[45][46]

There are several reasons for the unusual location of the A-10's General Electric TF34-GE-100 turbofan engines. First, the A-10 was envisioned to fly from forward air bases, often with substandard, semi-prepared runways that present a high risk of foreign object damage to the engines. The height of the engines decreases the chance that sand or stones will be ingested. This also allows engines to keep running while the aircraft is serviced and rearmed by ground crews, reducing turn-around time. Without the limitations imposed by engines, the wings could be mounted closer to the ground, to simplify servicing and rearming.[47]

The engines' high 6:1 bypass ratio provides the A-10 with a relatively small infrared signature, and their position directs exhaust over the tailplanes further shielding it from detection by heat-seeking surface to air missiles. The engines are angled upward by nine degrees to cancel out the nose-down pitching moment they would otherwise generate due to being mounted above the aerodynamic center of the aircraft. This avoids the necessity to trim the control surfaces against the force. The heavy engines require strong supports, so their pylons are connected to the airframe by four bolts.[47]

The A-10's fuel system components are protected in multiple ways. All four fuel tanks are located near the center of the aircraft, reducing the likelihood that they will be hit or have their fuel lines severed. The tanks are separate from the fuselage; thus, projectiles would need to penetrate the aircraft's skin before reaching the outer skin of the tank.[40][43] The refueling system is purged after use so that all fuel in the aircraft is protected from fire.[48] All fuel transfer lines self-seal if they are compromised; if a tank is damaged beyond its ability to self-seal, check valves prevent fuel flowing into the compromised tank. Most of the fuel system components are inside the tanks so that fuel will not be lost in case a component were to leak. Most importantly, reticulated polyurethane foam lines both the inner and outer sides of the fuel tanks, retaining debris and restricting fuel spillage in the event of damage. The other source of possible combustion, the engines, are shielded from the fuel system and the rest of the airframe by firewalls and fire extinguishing equipment. Even in the event of all four main tanks being penetrated and all contents lost, sufficient fuel is carried in two self-sealing sump tanks to allow flight for 230 miles (370 km).[40][43]

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