美国F-16猎鹰战斗机

General Dynamics F-16 Fighting Falcon

The General Dynamics (now Lockheed Martin) F-16 Fighting Falcon is a single-engine multirole 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 4,500 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 has key features 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 helps to make it a nimble aircraft. The F-16 has an internal M61 Vulcan cannon and 11 locations for mounting weapons and other mission equipment. The F-16's official name is "Fighting Falcon", but "Viper" is commonly used by its pilots, due to a perceived resemblance to a viper snake as well as 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

Overview

The F-16 is a single-engine, very maneuverable, supersonic, multi-role tactical fighter aircraft; it was designed to be a cost-effective combat "workhorse" that can perform various missions and maintain around-the-clock readiness. It is much smaller and lighter than 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 was the first fighter aircraft purpose-built to pull 9-g maneuvers and can reach a maximum speed of over Mach 2. Innovations include a frameless bubble canopy for better visibility, side-mounted control stick, and reclined seat to reduce g-force effects on the pilot. It is armed with an internal M61 Vulcan cannon in the left wing root and has multiple locations for mounting various missiles, bombs and pods. It has a thrust-to-weight ratio greater than one, providing power to climb and accelerate vertically.

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, stabilators, and ventral fins make use of bonded aluminium honeycomb structures and graphite epoxy lamination 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 placed so it was rearward of the nose but forward enough to minimize air flow losses and reduce aerodynamic drag.

Although the LWF program called for a 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. Changes in operational use and additional systems have increased weight, necessitating multiple structural strengthening programs.

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; 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 behind the single-piece "bubble" canopy of the cockpit. Split-flap speedbrakes are located at the aft end of the wing-body fairing, and an tailhook is mounted underneath the fuselage. A fairing beneath the rudder often houses ECM equipment or a drag chute. Later F-16 models feature a long dorsal fairing along the fuselage's "spine", housing additional equipment or fuel.

Aerodynamic studies in the 1960s demonstrated that the "vortex lift" phenomenon could be harnessed by highly swept wing configurations to reach higher angles of attack, using leading edge vortex flow off a slender lifting surface. As the F-16 was being optimized for high combat agility, 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, reduced by fuselage lift. The vortex lift effect is increased by leading edge extensions, known as

strakes. Strakes act as additional short-span, triangular wings running from the wing root (the juncture with the fuselage) 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, generating additional lift and allowing greater angles of attack without stalling. Strakes allow a smaller, lower-aspect-ratio wing, which increases roll rates and directional stability while decreasing weight. Deeper wingroots also increase structural strength and internal fuel volume.

Armament

Early F-16s 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 AAMs; a wide variety of air-to-ground missiles, rockets or bombs; electronic countermeasures (ECM), navigation, targeting or weapons pods; and fuel tanks on 9 hardpoints –six under the wings, two on wingtips, and one under the fuselage; two other locations under the fuselage are available for sensor or radar pods. The F-16 carries a 20 mm (0.787 in) M61A1 Vulcan cannon for close range aerial combat and strafing.

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. 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 inherent stability has to be overcome. 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 aerodynamic changes.

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 governing movement in the three main axes based on attitude, airspeed and angle of attack (AOA); these 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. Flight testing has 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 causes 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; the pitch limiter locks the stabilators at an extreme pitch-up or pitch-down attempting to recover, this 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, General Dynamics took the innovative step of eliminating mechanical linkages between the control stick and rudder pedals, and the flight 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

A key feature of the F-16's cockpit is the 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 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 tilted seat can accommodate taller pilots and increases G-force tolerance; however it has been associated with reports of neck ache, possibly caused by incorrect head-rest usage. Subsequent U.S. fighters have adopted more modest tilt-back angles of 20°. Due to the seat angle and the canopy's thickness, the ejection seat lacks 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 situation 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 look-down/shoot-down 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 processing, 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 indication, 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 radar (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 Block 40/42/50/52 aircraft to the (V)10 standard, providing all-weather autonomous detection and targeting for Global Positioning System (GPS)-aided precision weapons, SAR mapping and terrain-following radar (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. Northrop Grumman developed the latest AESA radar upgrade for the F-16 (selected for USAF and Taiwan Air Force F-16 upgrades), named 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 initial powerplant selected for the single-engined F-16 was the Pratt & Whitney F100-PW-200 afterburning turbofan, a modified version of the F-15's

F100-PW-100, rated at 23,830 lbf (106.0 kN) thrust. During testing, the engine was found to be prone to compressor stalls and "rollbacks," wherein the engine's thrust would spontaneously reduce to idle. Until resolved, the Air Force ordered F-16s to be operated within "dead-stick landing" distance of its bases. 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, later installed on Block 32 and 42 aircraft: the main advance being a Digital Electronic Engine Control (DEEC) unit, which improved reliability and reduced stall occurrence. Beginning production 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 1997 onwards to the "-220E" standard, which enhanced reliability and 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.

Variants

The F-16C (single seat) and F-16D (two seat) variants entered production in 1984. The first C/D version was the Block 25 with improved cockpit avionics and radar which added all-weather capability with beyond-visual-range (BVR) AIM-7 and AIM-120 air-air missiles. Block 30/32, 40/42, and 50/52 were later C/D versions. The F-16C/D had a unit cost of US$18.8 million (1998). Operational cost per flight hour has been estimated at $7,000 to $22,470 or $24,000, depending on calculation method.

F-16E/F

The F-16E (single seat) and F-16F (two seat) are newer F-16 variants. The Block 60 version is based on the F-16C/D Block 50/52 and has been developed especially for the United Arab Emirates (UAE). It features improved AN/APG-80 active electronically scanned array (AESA) radar, avionics, conformal fuel tanks (CFTs), and the more powerful GE F110-132 engine.

F-16IN

For the Indian MRCA competition for the Indian Air Force, Lockheed Martin

offered the F-16IN Super Viper. The F-16IN is based on the F-16E/F Block 60 and features conformal fuel tanks; AN/APG-80 AESA radar, GE F110-132A engine with FADEC controls; electronic warfare suite and infra-red searching (IRST); updated glass cockpit; and a helmet-mounted cueing system. As of 2011, the F-16IN is no longer in the competition.

F-16IQ

In September 2010, the Defense Security Cooperation Agency informed the United States Congress of a possible Foreign Military Sale of 18 F-16IQ aircraft along with the associated equipment and services to the newly reformed Iraqi Air Force. Total value of sale is estimated at US$4.2 billion.

F-16N

The F-16N is an adversary aircraft operated by the U.S. Navy. It is based on the standard F-16C/D Block 30 and is powered by the General Electric F110-GE-100 engine. However, the F-16N has a strengthened wing and is capable of carrying an Air Combat Maneuvering Instrumentation (ACMI) pod on the starboard wingtip. Although the single-seat F-16Ns and twin-seat (T)F-16Ns are based on the early-production small-inlet Block 30 F-16C/D airframe, they retain the APG-66 radar of the F-16A/B. In addition, the aircraft's 20 mm cannon has been removed, as has the ASPJ, and they carry no missiles. Their EW fit consists of an ALR-69 radar warning receiver (RWR) and an ALE-40 chaff/flare dispenser. The F-16Ns and (T)F-16Ns have the standard Air Force tailhook and undercarriage and are not aircraft carrier capable. Production totaled 26 airframes, of which 22 are single-seat F-16Ns and 4 are twin-seat TF-16Ns. The initial batch of aircraft were in service between 1988 and 1998. At that time, hairline cracks were discovered in several bulkheads and the Navy did not have the resources to replace them, so the aircraft were eventually retired, with one aircraft sent to the collection of the National Naval Aviation Museum at NAS Pensacola, Florida, and the remainder placed in storage at Davis-Monthan AFB. These aircraft were later replaced by embargoed ex-Pakistani F-16C/Ds in 2003. The original inventory of F-16Ns were previously operated by adversary squadrons at NAS Oceana, Virginia; NAS Key West, Florida and the former NAS Miramar, California. The current aircraft are operated by the Naval Strike and Air Warfare Center at NAS Fallon, Nevada.

F-16V

At the 2012 Singapore Air Show Lockheed Martin unveiled plans for the new

F-16V variant with the V suffix referencing its Viper nickname. It is to feature an active electronically scanned array (AESA) radar, a new mission computer and electronic warfare suite, and various cockpit improvements; this package can be retrofitted to previous F-16s, including the Block 60.

QF-16

In September 2013, an unmanned F-16 tested by Boeing and US Air Force, with two US Air Force pilots controlling the airplane from the ground as it flew from Tyndall AFB over the Gulf of Mexico.

Specifications

Crew: 1

Length: 49 ft 5 in (15.06 m)

Wingspan: 32 ft 8 in (9.96 m)

Height: 16 ft (4.88 m)

Wing area: 300 ft2 (27.87 m2)

Airfoil: NACA 64A204 root and tip

Empty weight: 18,900 lb (8,570 kg)

Loaded weight: 26,500 lb (12,000 kg)

Max. takeoff weight: 42,300 lb (19,200 kg)

Powerplant: 1 × F110-GE-100 afterburning turbofan

Dry thrust: 17,155 lbf (76.3 kN)

Thrust with afterburner: 28,600 lbf (127 kN)

Performance

Maximum speed:

At sea level: Mach 1.2 (915 mph, 1,470 km/h)

At altitude: Mach 2 (1,320 mph, 2,120 km/h) clean configuration

Combat radius: 340 mi (295 nmi, 550 km) on a hi-lo-hi mission with four 1,000 lb (450 kg) bombs

Ferry range: 2,280 nmi (2,620 mi, 4,220 km) with drop tanks

Service ceiling: 50,000+ ft (15,240+ m)

Rate of climb: 50,000 ft/min (254 m/s)

Wing loading: 88.3 lb/ft2 (431 kg/m2)

Thrust/weight: 1.095

Maximum g-load: +9.0 g

Armament

Guns: 1× 20 mm (0.787 in) M61A1 Vulcan 6-barrel Gatling cannon, 511 rounds Hardpoints: 2×wing-tip Air-to-air missile launch rails, 6×under-wing, and 3×under-fuselage pylon (2 of 3 for sensors) stations with a capacity of up to 17,000 lb (7,700 kg) of stores

Rockets:

4×LAU-61/LAU-68 rocket pods (each with 19×/7×Hydra 70 mm rockets, respectively)

4×LAU-5003 rocket pods (each with 19× CRV7 70 mm rockets)

4×LAU-10 rocket pods (each with 4× Zuni 127 mm rockets)

Missiles:

Air-to-air missiles:

2× AIM-7 Sparrow

6× AIM-9 Sidewinder

6× AIM-120 AMRAAM

6× IRIS-T

6× Python-4

Air-to-ground missiles:

6× AGM-65 Maverick

4× AGM-88 HARM

AGM-158 Joint Air-to-Surface Standoff Missile (JASSM)

Anti-ship missiles:

2× AGM-84 Harpoon

4× AGM-119 Penguin

Bombs:

8× CBU-87 Combined Effects Munition

8× CBU-89 Gator mine

8× CBU-97 Sensor Fuzed Weapon

4× Mark 84 general-purpose bombs

8× Mark 83 GP bombs

12× Mark 82 GP bombs

8× GBU-39 Small Diameter Bomb (SDB)

4× GBU-10 Paveway II

6× GBU-12 Paveway II

4× GBU-24 Paveway III

4× GBU-27 Paveway III

4× Joint Direct Attack Munition (JDAM) series

4× AGM-154 Joint Standoff Weapon (JSOW)

Wind Corrected Munitions Dispenser (WCMD)

B61 nuclear bomb

B83 nuclear bomb

Others:

SUU-42A/A Flares/Infrared decoys dispenser pod and chaff pod or

AN/ALQ-131 & AN/ALQ-184 ECM pods or

LANTIRN, Lockheed Martin Sniper XR & LITENING targeting pods or

up to 3×300/330/370/600 US gallon Sargent Fletcher drop tanks for ferry flight/extended range/loitering time or

UTC Aerospace DB-110 long range EO/IR sensor pod on centerline

Avionics

AN/APG-68 radar

MIL-STD-1553 bus

代表机型和战斗机分代

代表机型和战斗机分代 按照西方的战斗机分代划分方法 第一代：亚音速战斗机（喷气革命）——代表机型：美制F86、苏制米格15、中国歼5（前苏联米格15仿制型）等 第一代战斗机的判断依据：喷气式、亚音速，从此战斗机螺旋桨时代进入喷气时代，史称战斗机的“喷气革命”。 第二代：强调超音速性能的战斗机（超音速革命）——代表机型：美制F4、F5，苏制米格21、米格25（2代机的巅峰作品），中国歼7（前苏联米格21的仿制型）等 第二代战斗机的判断依据：战斗机速度首次超过音速，并且重视速度，认为速度越快战斗机越强（非能量机动原理设计），史称战斗机的“超音速革命” 第三代：可变后掠翼，米格—23和美制F—111单独划分一代称之为第三代。 第四代：强调中近距离空战和空空格斗的多用途超音速战斗机（能量机动革命）——代表机型：美制F15、F16、F14、F18，苏制米格29、苏27、苏30（苏27的改进型）中国歼10等，其中F15、F16、米格29、苏27被称为冷战末期统治天空的战斗机“四大天王”。 第四代战斗机的判断依据：符合能量机动原理设计的超音速多用途战斗机。关于能量机动原理，百度里很少有人回答准确什么是第4代战斗机，第三代战斗机就是用能量机动原理设计出来的战斗机。越南战争时期，美国空军发现，自己的F4速度比米格21快，但是屡屡被米格21击落，甚至在不利情况下难于脱身。这是为什么？。一些老的空军退役的飞行员和科学家一起合作研究，发现了“能量机动原理”，具体含义比较复杂，在此不多讲，能量机动原理即，同时具有最大动能和最大势能的战斗机在空战中取得胜利的可能性很高，这些人在综合了自二战以来所有战斗机格斗案例后的惊人发现，合理的解释了战斗机快和高之间的取舍。他们提出了和但是理论相悖的能量机动原理，指出，以后设计战斗机，速度并不是第一要求，飞机所有性能复合能量机动原理越好，他们也被当时不理解他们行为的人称为“战斗机黑手党”。但是F15制造出来以后，一鸣惊人，F15是第一款符合能量机动原理的战斗机，其后的F16服役，F16是第一款根据能量机动原理精确计算后制造的战斗机，自此美国空军进入4代机时代，前苏联几乎花了十几年才搞明白了能量机动原理。后来出来了苏27和米格29.。这里有一个争议，即F14，有人认为F14并不能符合能量机动原理设计，但是我们仍然把它算做第4代战机，因为当时正值“战斗机黑手党”和官员们争吵，另外，F14的可变后掠翼为能量机动原理提供了修正机会，所以仍然算第三代战斗机。史称战斗机的“能量机动革命” 第五代：强调隐身性能等4S标准的的多用途超音速战斗机——代表机型：美制F22“猛禽”、F35“闪电” ，俄罗斯在研的苏47（S37）“金雕”战斗机 第五代战斗机的判断依据：史称战斗机的“隐身革命”。 4S：Super Maneuverability；Super Sonic Cruise；Stealth；Superior Avioni cs for Battle Awareness and Effectiveness

F16 Aggresor(F16战斗机) 操作手册

F16 操作手册============飞行控制键=================== 副翼-----------------------------------[左右方向键] 安定升降面-----------------------------[上下方向键] 尾舵-----------------------------------[,][.] 开/关空气煞车--------------------------[B] 开/关轮煞车----------------------------[W] 0%节流阀-------------------------------[Shift][`] 10~90%节流阀---------------------------[Shift][1]~[9] 100%节流阀-----------------------------[Shift][0] 增加节流阀1%---------------------------[+] (如果已经是100%节流阀，则增加后燃器的推力等级) 降低节流阀1%---------------------------[-] (如果后燃器已开启，则降低后燃器的推力等级) 切换发动机状态(开/关)------------------[Shift][E] 开/关襟翼------------------------------[/] 收起/放下起落架------------------------[G] 自动飞行模式---------------------------[A] 自动降落模式---------------------------[L] 降低后燃器的推力-----------------------[Z]

美国战斗机(共5集)——05

F-105: 研制国家：美国，名称：雷公（Thunderchief） 一、概述： F-105是从一开始就作为战术空军司令部超音速战斗轰炸机而设计的第一种飞机，50年代初美国的战略思想是立足于打核战争，战术空军也要具备战术核轰炸能力。只制造了两架原型机F-105“雷公”于1952年作为共和航空公司的AP-63设计开始发展。1955年10月22日，第一架YF-105A（共两架）飞行，装一台普拉特?惠特尼J57-P-25 发动机。但在1956年5月出现的F-105B-1飞机上，采用了推力更大的J75-P-3 发动机和面积律的理论。这是1954财政年度最初15架飞机订货中的第3架飞机，其余的飞机（到F-105B-6）是到1957年完成的，供系统试验用。 F-105有B、D、F和G四种主要型别，共生产833架。其中F-105B是昼间战斗轰炸机，共生产78架。该机装备MA-8 火力控制系统，其主要部件是E-50（K-19）前置计算瞄准具、E-34（AN/APG-34）雷达测距器、E-30拉起轰炸计算机和KB-3照相枪。后来B型飞机又增加了AN/ARW-77“小斗犬”导弹控制器。F-105D是全天候战斗轰炸机，1959年6月首次试飞，共生产610架。该机装备AN/ASG-19 全天候火力控制系统和AN/ARW-77“小斗犬”导弹控制器，提高了对地攻击能力。系统的主要部件是瞄准具、搜索和测距雷达、拉起轰炸计算机和轰炸双向定时器。F-105F是双座教练和战斗轰炸机。1963年6月首次试飞，共生产143架。该机火力控制设备与D型相同。F-105G是由F-105F改装的反雷达攻击机。装备有各种电子战设备和AGM-45“百舌鸟”、AGM-78 标准反辐射导弹。各型F-105均于1965年全部停产。后来F-105的任务逐渐被变后掠翼战斗轰炸机F-111所代替。到1984年，所有的F-105退出了现役。 二、性能指标（F-105D） 尺寸数据：翼展10.65米，机长19.58米，机高5.99米，机翼面积35.76平方米、后掠角45度、展弦比3.18。 重量数据：空重12474千克，正常起飞重量17250千克，最大起飞重量23834千克。 性能数据：最大平飞速度（高空）M2.0/2120 千米/小时，（低空）M1.08，最大爬升率175米/秒，实用升限15850米，作战半径386～1460千米，转场航程3700千米。起飞滑跑距离800米，着陆滑跑距离700米。 武器装备：1 门20毫米6 管机炮（备弹1029 发），弹舱内可挂1 颗1000 千克或4 颗110 千克炸弹或核弹，翼下挂架可挂各种常规炸弹、“小斗犬”空对地导弹、“响尾蛇”空对空导弹等，最大载弹量5900 千克。 动力装置：1台J75-P-19W 涡喷发动机，加力推力107.8千牛，喷水加力推力117.9千牛。

F16详细介绍

机身上涂有美军八十年代后研究的浅灰色迷彩。机身前下部是发动机进气道，进气道下面挂装着“哈姆”导弹目。翼下最大的外挂物是副油箱，外侧是一枚AGM88“哈姆”反雷达导弹，最外侧的翼尖上挂着的ACMI空战战术 16最新型火控雷达| 巴基斯坦F-16 湾F-16战斗机页面 顾一下F-16的发展历程： 原型机。挂载4枚麻雀空空导弹，未装雷达，机鼻部后来经过扩大。 军新研制成功的F-15“鹰”重型战斗机正处于国际目光的焦点，因为它划时代的性能令人为之一振，美空军也为给了美国军方一个很大的难题：它太贵了，即使是财大气粗的美国也买不起太多的F-15；如果为了节省军费，会影响美军空战能力。为此，美军想到了一个解决方法：研制一种性能与F-15相比要求较低、价格便宜得多-15组成高低搭配，解决费用与性能之间的矛盾。 了ADF计划，即“先进昼间战斗机”计划。经过一番竞争，72年通用动力公司的原型机YF-16战胜了麦道公司低档配置”。随后YF-16被正式命名F-16“战隼”(FightingFalcon)。而YF-17则在后来的海军招标中，则反败，后命名为F/A-18“大黄蜂”。 战斗机史上占有独特的地位：它在气动外形上采用了三角翼加普通平尾、单垂尾、单发、翼身融合体的布局，其

常先进的设计，并被多种三代半、四代战斗机采用；在飞行控制方面，首次采用了革命性的静不稳定设计和四采用了侧杆布局，安排在飞行员座位右侧；座椅后仰30度，提高了飞行员抗过载的能力，保证了进行9G的机；座舱玻璃盖为前半球无框设计，提供了无遮挡的360度视野(这种设计沿用到了F-22“猛禽”上)。虽然ADF 电子设备要求不高，YF-16仍能装载大体积的航空电子设备，为改进留下了余地。F-16原型的主要武器装备为特林炮、AIM-9“响尾蛇”近距空空导弹以及AIM-7“麻雀”中距空空导弹。 飞行非常有戏剧性。74年1月8日，红、蓝、白三色涂装的YF-16被运到了加州爱德华空军基地。在主设计师H 组的指挥下，YF-16开始试飞。1月20日，由试飞员PhilOestricher进行高速滑行测试。突然YF-16发生滚中线，试飞员在紧急中灵活应对，操纵飞机飞离地面，稳定后再落回跑道，于是F-16的“首飞”完成了。2月2式的90分钟首飞，3天后突破了音速，6天之后达到了两倍音速。5月9日，试飞员NeilAnderson驾驶双座

战斗机划分标准

按照西方的战斗机分代划分方法 1：亚音速战斗机（喷气革命）——代表机型： xx制 F86、xx米格 15、中国歼5（前苏联米格15仿制型）等 第一代战斗机的判断依据： 喷气式、亚音速，从此战斗机螺旋桨时代进入喷气时代，史称战斗机的“喷气革命”。 2：强调超音速性能的战斗机（超音速革命）——代表机型： xx制 F4、F5，xx米格 21、米格25（2代机的巅峰作品），中国歼7（前苏联米格21的仿制型）等 第二代战斗机的判断依据： 战斗机速度首次超过音速，并且重视速度，认为速度越快战斗机越强（非能量机动原理设计），史称战斗机的“超音速革命”3：强调中近距离空战和空空格斗的多用途超音速战斗机（能量机动革命）——代表机型： xx制 F15、F 16、F 14、F18，xx米格 29、苏

27、苏30（苏27的改进型）中国歼10等，其中 F15、F 16、米格 29、苏27被称为冷战末期统治天空的战斗机“四大天王”。 第三代战斗机的判断依据： 符合能量机动原理设计的超音速多用途战斗机。关于能量机动原理，百度里很少有人回答准确什么是第3代战斗机，第三代战斗机就是用能量机动原理设计出来的战斗机。越南战争时期，美国空军发现，自己的F4速度比米格21快，但是屡屡被米格21击落，甚至在不利情况下难于脱身。 这是为什么？。一些老的空军退役的飞行员和科学家一起合作研究，发现了“能量机动原理”，具体含义比较复杂，在此不多讲，能量机动原理即，同时具有最大动能和最大势能的战斗机在空战中取得胜利的可能性很高，这些人在综合了自二战以来所有战斗机格斗案例后的惊人发现，合理的解释了战斗机快和高之间的取舍。他们提出了和但是理论相悖的能量机动原理，指出，以后设计战斗机，速度并不是第一要求，飞机所有性能复合能量机动原理越好，他们也被当时不理解他们行为的人称为“战斗机黑手党”。但是F15制造出来以后，一鸣惊人，F15是第一款符合能量机动原理的战斗机，其后的F16服役，F16是第一款根据能量机动原理精确计算后制造的战斗机，自此美国空军进入3代机时代，前苏联几乎花了十几年才搞明白了能量机动原理。后来出来了苏27和米格 29.。这里有一个争议，即F14，有人认为F14并不能符合能量机动原理设计，但是我们仍然把它算做第3代战机，因为当时正值“战斗机黑手党”和官员们争吵，另外，F14的可变后掠翼为能量机动原理提供了修正机会，所以仍然算第三代战斗机。史称战斗机的“能量机动革命” 4：强调隐身性能等4S标准的的多用途超音速战斗机——代表机型： 美制F22“猛禽”、F35“闪电”，俄罗斯在研的苏47（S37）“金雕”战斗机

美国空军第四代战斗机选秀内幕

美国空军第四代战斗机选秀内幕 已经作为展品的YF-23验证机 编者按：也许再过10年、20年，甚至半个世纪，我们才能真正认识到1991年美国空军ATF先进战术战斗机项目选型在世界航空史上划时代的意义。这次选型不仅带来了世界上第一种第四代战斗机，而且在战斗机发展史上首次将机动性置于此较次要的位置。为了再现当年那场影响深远的竞标，为了更深入的剖析美国空军以及美国航空界对未来空战的理解，本刊特邀请方方先生撰写此文。本刊曾于2005年第5期刊载《王者之翼》一文，结合本文，本刊希望给广大读者展现未来战斗机作战的一般理念及其运用到的航空技术蓝图。 口本刊特约撰述方方

1991年可以算是军用航空史上划时代的一年。就在这一年，美国空军下一代战斗机选型终十尘埃落定，第四代超音速战斗机完全浮出水面。这次选型对丁未来战斗机发展的意义无疑是极其深远的。 俗话说“成王败寇”，但1991年那次竞争的结果好像完全颠倒了过来。对于竞争结果的争论，即使在十四年后的今天也没有平息。竞争获胜的洛克希德YF-22没有赢得更多的赞誉，倒是落败的YF-23成了众多航迷(也许还有不少业界人士)心中的王者。不可否认，出现这种现象一个重要的原因是，YF-23那个超前卫的气动设计实在是太漂亮了! 那么在YF-23前卫的气动设计背后，究竟隐藏了什么呢?它究竟为什么输掉了这场里程碑式的竞争呢?也许我们可以一起探索一下现在，让我们回到上世纪70年代…… ▲先进战术战斗机计划(ATF) 1969—1970年，美围空军的FX计划(新一代重型战斗机，最终结果就是F-15)止处于最后选型阶段，但战术空军司令部已将眼光转向了FX的后继机上。在这段时间，战术空军司令部投资进行了代号TAC一85的项目研究，对FX后继机进行了初步探索。TAC-85研究报告于1971年完成，提出了一个概念原型——先进战术战斗机(ATF)。这只是一个相当粗略的概念，指望能从中看到今天F/A-22的影子是不可能的，但它的确是迈向第四代战斗机的第一步。此后数年问，战术空军司令部先后进行了一些小规模的研究计划，为ATF作技术储备。除了战术空军司令部外，其它相关部门也没闲着。位于莱特·帕特森基地的飞行动力实验

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F22 Design The Lockheed Martin F-22 Raptor is a single-seat, twin-engine, all weather stealth tactical fighter aircraft developed for the United States Air Force (USAF). The result of the USAF's Advanced Tactical Fighter program, the aircraft was designed primarily as an air superiority fighter, but has additional capabilities including ground attack, electronic warfare, and signals intelligence roles.[6] Lockheed Martin is the prime contractor and is responsible for the majority of the airframe, weapon systems, and final assembly of the F-22, while program partner Boeing provides the wings, aft fuselage, avionics integration, and training systems. The aircraft was variously designated F-22 and F/A-22 prior to formally entering service in December 2005 as the F-22A. Despite a protracted development as well as operational issues, the USAF considers the F-22 a critical component of its tactical air power, and states that the aircraft is unmatched by any known or projected fighter. The Raptor's combination of stealth, aerodynamic performance, and situational awareness gives the aircraft unprecedented air combat capabilities.[8] 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 missions due to delays in

F16全图解

首 页 | 论 坛 | 聊天室 | 咖啡屋 | 邮 箱 | 无 线 | 相 册 文 学 | 观 察 | 军 事 | 游 戏 | 娱 乐 | 图 片 | 数 码 | 写手之家 F16“战隼”轻型战斗机【全套图文解】 发贴者：第一观察员 2006/03/02 09:29 来源：军事-兵器论坛 点击：3503次 F16“战隼”轻型战斗机，美军主力轻型战斗机。1972年1月，美国空军正式提出“轻型战斗机”研制计划，目的是验证在战斗机上采用新技术，并没打算真的搞一个投产型号。四个月后，就从五家参加投标的公司中选定通用动力公司的401和诺斯罗普公司的P600两个方案，并签订合同要求两家公司各制造两架原型机，进行试飞竞争。通用动力公司的401方案军用编号为YF16；诺斯罗普公司的P600军用编号为YF17，原型机制成后，经过一年时间的竞争试飞。 screen.width-333)this.width=screen.width-333" border=0 dypop="按此在新窗口浏览图片"> 74年4月，美国政府决定从中选择一种继续发展，使之成为实用的轻型战斗机，与重型战斗机F15搭配使用，以弥补由于后者复杂昂贵而造成的购置数量不足，后来人们称此为“高低配置”。这一决定是美国空军原本没有预料到的，因此F16的出现可以说是有些偶然因素。75年1月，美国空军宣布通用动力公司的YF16中选，这就是F16战斗机的由来。而YF17虽然败阵，但是在后来的海军“高低配置”选择中，却又击败了F16，成为了后来的F/A18战斗机（主要的一个原因是海军认为单发动机的F16安全性不够，不足以应付严格的航母起降要求）。 第一架YF16原型机于73年12月出厂，74年2月首次试飞。F16生产型于1976年12月首飞，1978年底开始交付部队使用。现已成为美国空军的主力战机之一。国外用户包括比利时、丹麦、荷兰、挪威、以色列、埃及、希腊、土耳其、巴基斯坦、南韩、泰国、新加坡等国家，而中国台湾省也有订购。难怪F16有“国际战斗机”之誉。 F16的外型据说是从50多种方案中挑选出来的，采用悬臂式的中单翼，平面几何形状为切角三角形。前缘有随迎角和飞行速度的变化而自动下偏以改变机翼弯度的襟翼，采用这种设计可使飞机在大迎角是仍保持有效的升力系数，从而提高飞机的机动能力。后缘有全展长的襟副翼，既可象普通襟翼那样起增加升力的作用，又可以左右差动进行横向操纵。翼根前缘是大后掠角边条，可改善大迎角时的气动性能，同时可减轻飞机的结构重量。F16的外形相当漂亮，很有明星风范，也成为了美军“雷鸟”表演队的专用机。 机身为半硬壳结构，采用翼身融合体的设计，使机身与机翼平滑连接，不但可减小飞行阻力，提高升阻比，而且对结构强度有好处，可减重258千克，也对减小雷达反射面积很有好处。尾部有全动式平尾，平面形状与机翼相似，翼根整流罩后部是开裂式减速板。垂尾较高，安定面大，后缘是全翼展的方向舵。腹部有两块面积较大的安定翼面。起落架为可收放的前三点式。座舱盖为气泡形的，飞行员视野很好，内装零-零弹射座椅。控制系统采用四余度电传操纵技术，主要由信号转换装置、飞行控制计算机、电缆和动作装置组成。 早期的F16装一台普·惠公司的F100-PW-100型涡扇发动机，最大推力72.5千牛，加力推力111.1千牛；1984年后生产的F16改装通用动力公司的F110-GE-100发动机。 到目前为止，F16有十多种改型，包括： A 型单座战斗机、 B 型双座战斗教练机，两型产量达到1744架； 由A 型改进而来的C 型，和B 型的改进型D 型，C 、D 型加起来超过2200架； F16MLU 型，是F16的“中期寿命改进型”（MLU ）；台湾的F16使用了部分MLU 型的技术，装备APG66(V)3A 型火控雷达，能使用AIM7E “麻雀”中距空空导弹； 还有最先进的F16ES 型，1998年为阿联酋制造，在翼根上安装了两个外挂保形油箱，载油量大增；座舱盖前加装了一个光学搜索系统，外形于俄罗斯设计的产品有相似之处；能使用AIM120AAMAMR 先进中距空空导弹。

简介美国空军主要机型

简介美国空军主要机型 美军绘图炫耀庞大战力战机多种多样琳琅满目谷火 平原创09-28 14:02美国是目前世界上最强大的空军大国。仅仅美空军就拥有服役战机超过5000架，而且战机种类非常丰富。不仅有战斗机和轰炸机，预警机、运输机、侦察机、空中加油机等辅助性机型也大量装备使用。这些机种形成了有效的相互支持，构筑了强大的作战及防御网络系统。 据媒体报道，世界时事与地理网站绘制了三张示意图，涵盖了美国空军庞大的战机配置情况。这些图片直观的反映了美国空军的规模。 第一张图显示了战斗机及其支持机型。美空军目前有7个 F-22猛禽（Raptor）隐形战斗机队。F-22战斗机是单座双发动机隐形战斗机，可挂载AIM-9X红外空对空导弹、 AIM-120CD中程空对空导弹等武器，配备AN/APG-77主动相控阵雷达等尖端设备，是世界上战斗力最强的战斗机。2014年9月，F-22战斗机首次参战，参与了打击ISIS恐怖组织的行动。39个F-16战斗机队。F-16战隼（F-16 Fighting Falcon）是世界顶尖的轻型战斗机，机动性极强，可执行各种打击任务。F-16作战半径900公里，最大速度可达两倍声速，能在一分钟内爬升到15240米高空。 F-16可携带空对空和空对地导弹，以及各种炸弹。例如

AIM-7麻雀中程空对空导弹、AIM-9响尾蛇导弹、AGM-65 小牛空对地导弹、AGM-84鱼叉反舰导弹以及CBU-87、89集束炸弹等武器。12个A-10雷电（Thunderbolt）攻击机队。该机专门用于近距离空中支援，如攻击敌方坦克、地面人员等。A-10攻击机可挂载6枚AGM-65小牛空对地导弹、2 枚AIM-9L响尾蛇飞弹、集束炸弹等，可携带电子干扰设备。A-10参加了波斯湾、科索沃、阿富汗、利比亚战争等，表现出极强的生存力，以及对地打击能力。 第二张图描绘了庞大的空中加油平台、轰炸机及作战训练机群。该网站总结，美空军一共有30个空中加油机队，扩大 了空战领域，保证了美军全球到达能力的实现。 11个轰炸机队装备了B-1 枪骑兵（Lancer）、B-2幽灵（Spirit）隐形战略轰炸机，以及B-52H 「同温层堡垒」（Stratofortress）远程战略轰炸机三个机种。B-52的服役期间已经长达60年，但是经过不断更新，仍发挥着重要的作用。 第三张图是关于运输机队，包括20个C-17全球霸王III （Globemaster III）和38个C-130大力神（Hercules）运 输机队。（加）

全球最先进战斗机排名榜

全球最先进战斗机排名榜 第一名：F-22“猛禽”战机 F-22是世界上致命打击性能最好的战斗机，是美国空军的最重要机种，F-22“猛禽”是一款第五代战斗机，以其高机动性、传感器融合性、超音速巡航和致命攻击能力成为了世界上最顶级战机。 第二名：俄罗斯第五代战机T-50

俄罗斯第五代战机T-50为单座双发重型战机，具备隐身性能好、起降距离短、超机动性能、超音速巡航等特点。其超音速巡航速度可达每小时1450千米，作战半径1100千米，战斗负荷可达 6吨，内置3个武器舱，能实现飞行性能和隐身性能的良好结合 第三名：F-35战机 F-35“闪电II”是一款由美国洛克希德·马丁公司设计生产的单座单发动机多用途战机，能够负担近空支援、F-35闪电II(19张)目标轰炸、防空截击等多种任务。 第四名：苏35战机

苏-35是第4.5代重型战机，具有远程，多用途，空优和打击等特性。和苏-30有同样血统设计，有相似性能特征和零件；也可说是苏-30的一种特制版。更助长了苏-35BM型的研发。目前苏-35只有少量的五架服役于俄罗斯空军。 第五名：F/A-18“大黄蜂”战机 F/A-18“大黄蜂”战机是一种具备最好气动性能和大攻角能力的多用途战术飞机，被誉为“美国尊严守护者”。这架战机率先使用数字复用航空总线和多功能显示器，可使飞行员在瞬息万变的战斗环境中更加灵活的执行动作。

第六名：“阵风”战机 “阵风”战机具备众所周知的空对空战斗能力，是一种占尽空中优势的战斗机。“阵风”战机由法国军机、商务机生产商达索(Dassault)飞机公司设计开发。这款飞机支持“光谱”电子战系统，可抵御地面和空中的威胁。这款战机还可以协助生成远距离拦截和锁定所需要的实时三维地图。 第七名：“鹰狮”战斗机 “鹰狮”战机具有八个可装载导弹和炸弹的挂载点，是一种轻型战机，以其鸭式三角翼设计和高机动性著称。这架战机支持一个复杂的PS-05A型脉冲多普勒X射线雷达，可以侦测120公里外的目标。“鹰狮”也可以通过发射空空导弹进行超视距攻击。

美国F-16猎鹰战斗机

General Dynamics F-16 Fighting Falcon The General Dynamics (now Lockheed Martin) F-16 Fighting Falcon is a single-engine multirole 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 4,500 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 has key features 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 helps to make it a nimble aircraft. The F-16 has an internal M61 Vulcan cannon and 11 locations for mounting weapons and other mission equipment. The F-16's official name is "Fighting Falcon", but "Viper" is commonly used by its pilots, due to a perceived resemblance to a viper snake as well as the Battlestar Galactica Colonial Viper

第四代战斗机 简介

第四代战斗机 百科名片 第四代战斗机 第四代战斗机是目前正在研制的最先进的战斗机，它的技术战术指标是根据现代高技术局部战争的实战经验提出的。现代战争已经由过去的单一兵器的对抗转变为海、陆、空军三位一体全方位的较量，而其中最重要的则是制空权的争夺。 目录 概述 代表机型和战斗机分代 1：亚音速战斗机 2：强调超音速性能的战斗机 其他相关 第一、二、三、四代战斗机的概况区别 第一代 第二代 第三代 第四代 中国第四代战斗机 相关报道 节目实录 中国四代战斗机-歼20 概述 代表机型和战斗机分代 1：亚音速战斗机 2：强调超音速性能的战斗机 其他相关 第一、二、三、四代战斗机的概况区别 第一代 第二代 第三代 第四代 中国第四代战斗机 相关报道 节目实录

中国四代战斗机-歼20 展开 编辑本段概述 由于通讯手段和电子雷达、预警设备的发展，使现代战争的战场空前扩大，为了适应这一变化，飞机的作战半径也应该相应增加，为此对第四代战斗机提出了超音速巡航的要求；而为了应对敌方强大的电子雷达系统和防空导弹的威胁，飞机具有隐身能力也是必不可少的；隐身无疑提高了飞机的生存率。综合起来对第四代战斗机往往要求具有下列战术技术性能： 第四代战斗机 第四代战斗机的标准通常称为4S标准，因为这四个标准的英文单词都以S开头，即Super Maneuverability Super Sonic Cruise Stealth Superior Avionics for Battle Awareness and Effectiveness 翻译成中文就是―超机动性‖、―超音速巡航‖（某些翻译为不开加力都超音速巡航，实际上是多余的，因为战斗机巡航状态一般不用加力，加力一般用于对空格斗冲刺等任务）、―隐身能力‖和―高级战役意识和效能的航空器‖（直译）。 关于Superior Avionics for Battle Awareness and Effectiveness国内有一些译作―高可维护性‖，―超视距打击‖等等。按照F-22的制造商洛克希德马丁公司的官方文档（http://www.lockheedmartin. com/data/assets/corporate/press-kit/F-22-Brochure.pdf）的解释，更倾向于解释为―高信息优势‖，也就是―网络中心战‖。即让战斗机成为网络中心战的一个结点，与其他作战单位共享战斗情报，让战斗机飞行员更充分的了解自身所处的环境。关于翻译成―超视距空战‖的说法，有些网友提出了为什么BVR的疑问，认为不能翻译成超视距空战。―BVR‖，直译为Beyond Visual Range（视距外打击），是一些二代战斗机（比如F-4E）和3代机已经具备的能力，但是因为雷达等硬件和其他配套软件等技术原因，无法使BVR能力达到实用化。如如F15使用远距空空导弹，在视距外攻击的准备时间很短，一旦对方战机接近躲过第一波超视距打击，就进入中近程范围，甚至往往仍然需要空空格斗决定胜负，BVR 只是一种字面意义上都描述。在3代机时代，BVR更多只能说明在空空导弹技术上达到要求，但是对于战机，远远没有进入超视距攻击时代。相对于二代机BVR能力的―超前‖想法，3代机重新回到了重视中距和近距空空格斗能力，能量机动原理（即区分二代机和三代机标准的重要标志）也随之诞生。Superior Avionics for Battle Awareness and Effectiveness直译是―高级战役意识和效能的航空器‖，根据洛马公司的倾向性解释，可以翻译成网络中心战情况下的战场意识能力，即―多次持续摆脱敌机后进入到视距外范围，利

美军F22战机在福建被击落

美军F22战机在福建被击落？中国到底做了什么美军F22战机在福建被击落? 导读：前些日子，说福建某处坠毁了一架战机，并有网友发来了一些用手机照的现场照片，其中用一张就是下面左图。图中为一名飞行员使用降落伞降落的画面。注意，这张左图并不是原图的全部，原图上的背景还有当地的一些砖瓦建筑。从建筑的风格来看，一定是中国风格的常见的那些建筑，所以可以判断是在中国内地。请大家注意左图的降落伞的样式。 作为航空大国的美国，战机的弹射座椅是成系列化发展的，很多型号飞机的弹射座椅是相同或相似的，具体型号我不记得了，还请网友提示答案。那么，中国飞行员的降落伞的样式(这里主要指降落伞的花纹)是否与美军的相同，笔者不是很清楚，但是还主要倾向于花纹是不同的。在这个假设成立的前提下，笔者大胆猜测，这架飞机是美军的。 那么有的网友说，美国的飞机卖了很多国家和地区，能不能是他们的?我们来看看中国附近国家装备美国战机的国家：日本、韩国、台湾。日本、韩国的美国战机如果飞到中国大陆，已经接近他们作战半径的极限，而且日本与中国关系紧张，中国也不惯日本毛病，如果日本战机入侵，将会引起中国政府极大的报复行动，否则难以以谢国人。同理，韩国的原因也与上面类似。那么，能不能是台湾

呢?我看可能性不大。台湾那边台独得叫嚣愈演愈烈，如果再加上战机入侵，那么中央政府就是想和平也是忍无可忍的了。陈水扁也不会那么愚蠢。所以，综合来看，只能是美军。 那么美军哪型飞机有如此能力?我看只有F-22。试问F15、F16之类的敢来吗?我大胆猜测，这是美军为了测试我防空系统能力的一次大胆行动。美军之所以有这个行动我看主要的原因是中国已经为解决台湾问题做足了准备了，但是美军并不十分了解这些准备的水平如何?那么如果大陆万马奔腾的解决台湾问题时，美军能不能来驰援呢?会有什么后果呢?最好的判断方法就是飞过去试一试，因为即使美军驰援台湾，刚开始的主要手段还是飞机。如果飞机不成，美军登陆台湾是不可能的了。 结果F-22飞来了，具体的方式我认为还是利用F-22出色的隐身性能，采取无线电静默，低空飞行的方式，对大陆沿海进行一次测试。看样子美军过高的估计了F-22的性能，认为在距离大陆沿海较近的时候，再加上F-22有半小时的超音速巡航的能力，对大陆来一次10分钟左右的模拟突袭还是比较有把握的。最次，被发现了，也很难被打下来，大陆也只能自吞苦果，顺便也展示一下美军的威风，对大陆进行战略恐吓。 但是，他们想错了。F-22如果在远距离大陆的雷达即使发现了看样子还很难锁定的，可这次美军似乎有些玩过界了，太相信F-22了。结果大家都知道了。政府对外是没有什么说法的，对内只是传

美式战机大全

F-1“FURY”(狂怒 US Navy FJ) 北美公司研制的单座舰载战斗机，外形与F-86“佩刀”很相似。可携带AIM-9“响尾蛇”空空导弹，内置4门20mm机炮。FJ-2/FJ-3/FJ-4统一编号为F-1，FJ-1并不在内(可能是FJ-2开始是FJ-1的重 大改型，由平直翼改为后掠翼)。 F-2“BANSHEE”(女妖 US Navy F2H) 麦克唐纳公司研制的单座舰载战斗/侦察机，由FH-1“鬼怪”改进而成。“女妖”这个绰号的来源很有意思：F-2高速飞行时两具蜗轮引擎会发出凄疠的尖叫声。机鼻装备了雷达，还有自动驾驶

仪、增压座舱、弹射座椅等新式装备。F-2是朝鲜战争中的主力舰载轰炸机。 F-3“DEMON”(魔鬼 US Navy F3H) 麦克唐纳公司研制的第一种后掠翼喷气式战斗机，也是第一种只带导弹不用机炮的战机。单发、近音速全天侯战斗机，共生产了522架。

F-4“PHANTOM II”(鬼怪II) 麦克唐纳与道格拉斯公司合并后研制的双发双座重型战斗机，是一个庞大的“鬼怪”家族，也是第一种海空军的通用战斗机。派生型繁杂。F-4共生产了5000架，至今仍有800架在埃及、德国、希腊、以色列、日本、韩国、西班牙、土耳其服役。

F-5A/B“Freedom Fighter”(自由战士)F-5E/F“Tiger II”(虎) 诺斯罗普研制的双发超音速轻型战机，主要供外削，这从F-5A“自由战士”这个绰号就可以看出。F-5E/F有小部分在美空军服役，主要用途是假想敌。

F-6“SKYRAY”(天光 US Navy F4D) 道格拉斯公司研制的三角翼战斗机。装备20mm机炮和响尾蛇空空导弹以截击敌机。 YF-7A“Sea Dart”(海标枪 US Navy YF2Y-1) 康维尔公司研制的水上喷气式战斗机。这是一种非常奇特的战斗机，总共制 造了5架，2号机试飞中坠毁。

战斗机非常规机动飞行动作分析

战斗机非常规机动飞行动作分析 自从片面地追求高空高速的美国飞机在越南战场上吃足了苦头后，美国开始对其第三代战斗机提出较高的机动性要求。从首先开始服役的F14为发端，F16、15和18和法国的幻影2000以及前苏联时期开始研制的米格29和苏27等三代战机等也都以较高的机动性闻名于世。由于汲取了越南战争的经验与教训，各国都普遍强调空战机动性，甚至麦道公司为他们的F15提出不为对地攻击付出一磅重量。当时的主要措施是采用提高飞机推重比和降低翼载、配备襟翼和缝翼等增升装置的办法。并多数应用了边条翼和翼身融合体技术，在较晚出现的F16、18、幻影2000、米格29、苏27等飞机还应用了放宽静稳定度等技术，更进一步提高了战机的指标。这些性能出众的飞机在多年的战争中普遍战绩辉煌。获得了一致的好评。 随着第四代空优战机，美国的F22的飞机的研制成功。超音速巡航、隐身设计、非常规机动等标准被人们广泛认同。其中，非常规机动中又以大迎角过失速机动(PSM)（超过一般的可控临界迎角与速度且仍然有能力完成可操纵的战术机动）飞行以及直接力控制非常规机动（DFCM）最被大家熟悉。而它们的实现又必须以大推重比发动机、先进随控布局（含电传操纵）、推力矢量喷管为基础。 在进行空战机动时，为了能帮助飞行员迅速掉转机头指向，及时锁定对方，以提高对攻击对象的命中概率，除在辅助增升装置上做文章外，最直接有效的办法就是扩大使用迎角。这就要求对大迎角的饶流现象及其规律做充分了解。现代战斗机在做大迎角机动飞行时，飞机的姿态、迎角、侧猾角、滚转等变化迅速，这就必须在已十分复杂的流场中再引进一个新的变量：时间。对于振荡或瞬变运动，由机身、机翼、舵面、和其他操纵面等所产生的涡流的强度、位置、轨迹、性质等不仅是迎角的函数，也是时间的函数。也就是说必须将时间的历史效应做为一个变量，予以考虑。而不再能忽视其作用。 在四代战机中敏捷性较之三代时期获得了明显的重视。敏捷性(或机敏性)是在机动性的基础上随着现代战斗机及其机载雷达、火控系统和导弹武器的迅速发展而提出的新概念。大家知道飞机的机动性是指飞机在一定的时间间隔内改变其飞行速度、飞行高度和航向的能力。战斗机的机动性包括垂直机动性和水平机动性，而水平机动性又包括水平加、减速性能和水平盘旋性能。垂直机动性在垂直片面内的平飞加减速和俯冲、跃升、筋斗等。飞机的盘旋性能可以反映飞机的空战性能，其代表指标是盘旋过载。如果要定量分析，可以以单位能量、能量高度、剩余推力、单位剩余推力，翼载、过载，升阻比等为衡量指标。 飞机的飞行动作是以位能、功能、阻力消耗和发动机推力这几种主要能量形成的系统。机械能的变化是与推力T和阻力D密切相关的，推力和阻力之间的差额是剩余推力。飞机单位重量所拥有的剩余推力就被叫做单位剩余推力。公式为SEP=

简介F16机座舱

各位弟兄好: 小弟為各位簡介F-16機座艙配置及電門開關介紹,順便補充自己的心得,有興趣的隊友們可一起探討,當然不是每個電門開關我都清楚,知道的隊友,煩請補充.........(由於網路上尺度關係,僅簡介電門名稱,若在eFALCON110手冊上有提及,我會詳細寫出來)分成8個PARTS,介紹順序為左至右,按照號碼順序... PART 1

PART 1(1~48) 1:按下可測試在主警告燈面板之火警/超溫警示燈是否作用正常.... 2:氧存量測試,往上推,氧錶指針會轉動,當指針低於0.5升以下時,低氧警告燈亮,放開按鈕指針則會自動顯示氧存量. 3:按下可測試主警告面板燈及機內所有指示燈是否作用正常,及語音警告是否作用良好. 4:攻角,空速管,大氣資料探管加溫測試開關. (高空中,由於低溫及空速快,若無加溫相關裝備,則會因此結冰,導致作用不良) 5:EPU測試開關. 6:飛操系的ABCD燈,飛操自測時,會自行顯示. 7:飛操電瓶開關. 1~7 可歸類為測試面板 8:抗G衣測試按鈕.(好像超過4個G時自動作用) 9,10,11:Roll,Yaw,Pitch 配平微調. 12:機外燈光總開關. 13:防撞燈開關.(像閃光燈的顏色,會一閃一閃的,於直尾翅頂端) 14:控制航行燈(左紅右綠)閃爍與否. 15,16:翼尖及機身燈光亮度調整,往上燈光較亮,往下燈光較暗,Off則燈光無作用. 17:編隊燈亮度調整. 18:空中加油燈亮度調整. 12~18為機外燈光面板 19:抗G管.(與抗G衣連接) 20:座艙罩搖柄(當無法電動升起時使用). 21:主燃油電門.(打開燃油供應閥,供油至發動機) 22:燃油惰化電門.(當機內油箱起火,可使用機內滅火裝置(海龍)滅火). 23:Eng Feed 電門(於normal可啟動油箱pump,保持飛機之載重平衡) 24:空中加油電門. 25:敵我識別功能作用開關. 26:mode4電門.