GUNs wikipedia

M24 Sniper Weapon System

2010-07-24T13:10:00.000-07:00

The M24 Sniper Weapon System (SWS) is the military and police version of the Remington 700 rifle, M24 being the model name assigned by the United States Army after adoption as their standard sniper rifle in 1988. It is also used by the Israeli Defence Forces. The M24 is referred to as a "weapons system" because it consists of not only a rifle, but also a detachable telescopic sight and other accessories.

The M24 was designed to use the "long-action" version of the Remington M700 BDL. This was chosen because the Army wanted the ability to rebarrel the rifle from 7.62 NATO to the .300 Winchester Magnum cartridge if needed, which required a long action receiver. The .30-06 cartridge was never intended to be used by the M24 SWS. Due to using a short action cartridge in a long action receiver and magazine box, rounds must be pushed to the rear of the magazine in order to ensure reliable feeding.

It originally came tapped for the Leupold Ultra M3 10x40mm fixed-power scope, which came with a circle-shaped etched-glass reticle. This was later replaced in 1998 by the cheaper Leupold Mk.4 LR/T M3 10x40mm first focal plane fixed-power scope with a mil-dot reticle.

N.B.: The first number is the scope's magnification (10) and the second number in millimeters (40mm) is the diameter of the objective lens. A fixed power scope has only one magnification (e.g., 10x) and a variable power scope can be adjusted to focus between a range of magnifications (e.g., 3-9x is adjustable from a minimum power of 3x to a maximum power of 9x).
It comes with a detachable Harris 6-9" BRM-S swivel bipod unit.

The M24 SWS was to be replaced with the M110 Semi-Automatic Sniper System, a contract awarded to Knight's Armament Company. However, the Army still continued to acquire M24s from Remington until February 2010 and the M24 is being upgraded to the A2 standard in many cases, and continues to serve.

Specifications

Type	Sniper rifle
Place of origin	United States

Service history
In service	1988–present
Used by	See Users
Wars	Operation Desert Storm Operation Iraqi Freedom Operation Enduring Freedom
Production history
Designed	1988
Manufacturer	Remington Arms
Produced	1988–c.2010
Variants	M24A2, M24A3
Specifications
Weight	5.4 kg (11.88 lbs) empty, w/. sling, without scope (M24) 7.3 kg (16 lbs) max weight with day optical sigh, sling swivels, carrying strap, fully loaded magazine 5.6 kg (12.32 lbs) empty, w/. sling, without scope (M24A3).
Length	1,092 mm (43 in) (M24A1, M24A2); (46.5 in) (M24A3)
Barrel length	660.4 mm (24 in)(M24A1, M24A2); (29 in) (M24A3)

Cartridge	7.62x51mm NATO (M24A2), .300 Winchester Magnum (M24A1), .338 Lapua Magnum (M24A3)
Action	Bolt-action
Rate of fire	@20 rpm
Muzzle velocity	2,580 ft/s (790 m/s) w/M118LR Sniper load (175 gr.)
Effective range	800 metres (875 yd) (7.62x51mm) 1,500 metres (1,640 yd) (.338 Lapua Magnum)
Feed system	5-round internal magazine (M24A1), 10-round detachable box magazine(M24A2), 5-round detachable box magazine(M24A3)
Sights	Telescopic; detachable backup iron sights

Sights: Leupold Ultra M3 10 x 40mm fixed power, Leupold Ultra M3A 10 x 40mm fixed power, or Leupold Mk.4 LR/T M3 10 x 40mm fixed power scope. Detachable emergency Redfield-Palma International back-up iron sights, fitted with tabs that fit into slots machined into the front and back of the barrel.

Barrel: Made of 416R Stainless Steel. The bore twist is 1-turn-in-11.25 inches [1:285.75 mm] and the rifling is 5 radial lands and grooves (5-R) with a right-hand (RH) twist. Because of the odd number of lands, none of the lands are 180° apart, i.e. in direct opposition. This results in less bullet deformation, which (at least in theory) produces more consistent point of impact. In 5-R rifling, the "side" of the land is cut a a 65° angle, rather than 90° in conventional rifling. This results in less barrel fouling, and more consistent point of impact, compared to conventional rifling when relatively high numbers of rounds are fired between cleaning, as might be expected in military applications.

Stock: H-S Precision PST-11 stock. The stock secures the barrel via an aluminum bedding block to keep it rigid. A twin-strut extension that pulls out of the butt is adjustable for a 2-inch [50.8mm] length-of-pull. This is effected by a thick wheel on a central grooved pillar for adjusting the length and a thin locking ring behind it locks the thick wheel in place. The latter is notorious for failing, causing the extension to slide back and forth. Also a styrofoam core designed to reduce the stock's weight would absorb water if it was carried in the rain or soaked in a stream or river, making the weapon heavy and unbalanced.

Accuracy: According to MIL-R-71126(AR), the M24 shall achieve the accuracy results stated below when using M118 Special Ball and fired from a Government approved machine rest. The average mean radius shall be less than or equal to the following values:

200 yards (182.9 m): 1.3 inches
200 metres (218.7 yd): 1.4 inches
300 yards (274.3 m): 1.9 inches

Maximum effective range is given as 875 yards (800 meters), but record shots have been made with the M24 at over 1,000 metres (1,094 yd). Meanwhile, the standard optical sight has a maximum elevation adjustment of 1,000 metres (1,094 yd).

Match-Grade Ammunition

7.62 x 51mm M118 Match Grade A 173-grain round.
7.62 x 51mm M118LR Long Range A 175-grain round using Sierra MatchKing Hollow Point Boat Tail projectiles.
- 7.62mm M118 Long Range Performance Data:
- Muzzle velocity (nominal): 2,580 f/s (786 m/s)
- Chamber pressure (typical): 52,000 psi (358.6 MPa)
- Action time (max): 4 ms
- Average horizontal spread at 1,000 meters: 10.3 in (0.984 MOA)
- Average vertical spread at 1,000 meters: 14 in (1.337 MOA)

According to JBM Ballistics, using the G7 ballistic coefficient provided by Bryan Litz, the 7.62mm M118 Long Range 7.62x51mm NATO cartridge, when fired at its nominal muzzle velocity of 786 m/s (2,580 ft/s), should have approximately 878 m (960 yd) supersonic range under International Standard Atmosphere conditions at sea level (air density ρ = 1.225 kg/m³).

7.62 x 51mm MK 316 MOD 0 Special Ball, Long Range A 175-grain round consisting of Sierra MatchKing Hollow Point Boat Tail projectiles, Federal Cartridge Company match cartridge cases and Gold Medal Match primers and an undisclosed modified extruded propellant. The 7.62 x 51mm MK 316 MOD 0 Special Ball, Long Range cartridges have an accuracy requirement based around 10-round shotgroups.
- The average extreme spread radius for 10-round shotgroups shall be less than or equal to the following values:
- 600 yd: 7.0 in (first Production Lot). This equates to a ≤ 1.1 MOA requirement at 548.6 m.
- 300 yd: 3.5 in (after first Production Lot). This equates to a ≤ 1.1 MOA requirement at 274.3 m.

The maximum muzzle velocity standard deviation is set at 15 ft/s (4.57 m/s). Information published on acceptance tests regarding five MK 316 MOD 0 cartridge production lots indicated a sub 2.4 in at 300 yd performance. This equates to a sub 0.8 MOA performance at 274.3 m for the listed ammunition lots

M24 Variants

XM24A1

An experimental variant re-chambered for the .300 Winchester Magnum (7.62×67mm) round. It was not adopted by the US Army due to concerns that operatives in the field would not be able to acquire the special ammo. Also, the available .300 Winchester Magnum ammo that was procured sometimes misfired due to incompletely-burned propellant in the longer cartridge.

M24A2

Remington has developed an improved version of the M24 rifle, known as the M24A2. The A2 model features a detachable 10-round magazine, top-mounted and adjustable side-mounted Picatinny rails (advertised by Remington as "MARS", or Modular Accessory Rail System), barrel modifications designed to accommodate a sound suppressor, and an improved H-S Precision PST-25 stock with adjustable cheek height and length of pull. Existing M24s can also be converted into M24A2s, which replaces the stock and adds the new detachable magazine feed. The conversion requires a rebarreling of the weapon so it could take the OPS silencer.

M24A3

Remington has also developed the M24A3 SWS, a variant of the M24 chambered for the .338 Lapua Magnum round (8.58x70mm) and feeding from a 5-round detachable box magazine.It comes tapped for the Leupold Mk. 4 M1LR/T 8.5 - 25 x 50mm Variable Power day scope. It can also use detachable front and rear Back-Up Iron Sights in an emergency (BUIS units are standard accessories that can be fitted to the Picatinny Rail that runs on the top of the receiver and along the barrel).

U.S. Army 2009 solicitation for a M24 reconfiguration

The U.S. Army has put out a solicitation in May 2009 for reconfiguring M24 Sniper Weapon Systems currently available in Army inventory consisting of a:

Rebarreling/rechambering the SWS's barrel optimized to accommodate Mk 248 (DODIC A191) .300 Winchester Magnum ammunition.
Replacement of existing weaver rails with a MIL-STD-1913 rail capable of accommodating both a day optic and in-line forward mounted, AN/PVS-26 (NSN 5855-01-538-8121) image intensified (I2) night vision device.
Reconfiguring the stock with a stock that incorporates a detachable box magazine, adjustable comb and length of pull.
Addition of a detachable sound suppressor as well as any necessary barrel modifications required for a sound suppressor interface.
Replacement of the existing day optic sight (DOS) and rings with an Army specified variable power day optic and compatible rings.

The US government purchased MK 248 MOD 1 .300 Winchester Magnum match-grade ammunition in 2009 for use in .300 Winchester Magnum sniper rifles like the U.S. Navy Mk.13 SWS or reconfigured M24 SWS's. This ammunition was developed as a .300 Winchester Magnum Match Product Improvement (PIP) and uses the 14.26 g (220 gr) Sierra MatchKing Hollow Point Boat Tail (HPBT) very-low-drag bullet fired at a nominal muzzle velocity of 869 m/s (2,850 ft/s) ± 15.2 m/s (50 ft/s). According to the U.S. Navy this ammunition should increase the maximum effective range of .300 Winchester Magnum sniper rifle systems to 1,370 m (1,500 yd), decrease wind defection on bullets in flight and use a reduced muzzle flash propellant that remains temperature stable across an operational temperature range of -32 °C tot 74 °C (-25 °F to 165 °F). According to JBM Ballistics, using the G7 ballistic coefficient provided by Bryan Litz, the Mk 248 MOD 1 .300 Winchester Magnum cartridge, when fired at its nominal muzzle velocity of 869 m/s (2,850 ft/s), should have approximately 1,286 m (1,406 yd) supersonic range under International Standard Atmosphere conditions at sea level (air density ρ = 1.225 kg/m³).

M24 SWS system components (U.S. Army photo).

Users

Israel: Israel Defense Forces.
Japan
Lebanon
United States: Used by the US Army. Also used by various police SWAT teams.

JF17 Thunder

2010-07-21T14:45:00.000-07:00

The JF-17 Thunder, also designated Chengdu FC-1 Xiaolong (English: Fierce Dragon; pinyin: Xiāo Lóng) is a single-engine, light-weight multi-role combat aircraft developed jointly by the Chengdu Aircraft Industries Corporation (CAC) of China, the Pakistan Air Force and the Pakistan Aeronautical Complex (PAC). It is designated as "JF-17" by Pakistan, which is short for "Joint Fighter-17" and as "FC-1" by China, which is short for "Fighter China-1".

The JF-17 was developed primarily to meet the requirements of the Pakistan Air Force for a low-cost, medium-technology, multi-role combat aircraft as a cost-effective replacement for its ageing mixed fleet of Nanchang A-5, Chengdu F-7P/PG and Dassault Mirage III/V fighters and also have export potential to air forces of other developing countries as a cost-effective alternative to hi-tech but expensive Western fighters.

Pakistan and China signed the Letter of Intent for the joint development of the JF-17 (then called "Super-7") in 1998, followed by the signing of the Contract in 1999. The project got delayed due to the inability to find an avionics and radar package. In 2001, the Pakistan Air Force recommended that the airframe design be de-coupled from the avionics and radar systems for the aircraft to avoid further delay. This resulted in a fresh impetus to the project and the design was finalized and 'frozen' in 2001. The maiden test flight of the first prototype took place during 2003 in China, later test flights with a modified design with Diverterless Supersonic Intakes (DSI), and a modified tail design took place in 2006. Deliveries to the Pakistan Air Force for further flight testing and evaluation began in 2007,[9] the aircraft's first aerial display also taking place that year in Islamabad, Pakistan. The Pakistan Air Force officially inducted its first JF-17 squadron on 18th February 2010.

The JF-17 is expected to cost approximately US$15 million per unit. The Pakistan Air Force has announced that it has a confirmed order for 150 JF-17s, which may increase to 250 aircraft. The JF-17 will replace Pakistan's MiG-21-derived Chengdu F-7, Nanchang A-5 and Dassault Mirage III/Mirage V aircraft currently in service. Azerbaijan, Zimbabwe and eight other countries have expressed interest in purchasing the JF-17 at a recent military exhibition in Pakistan, according to an official

Development

The JF-17 was designed and developed jointly by China's Chengdu Aircraft Industry Corporation (CAC), the Pakistan Air Force and Pakistan's Pakistan Aeronautical Complex. The project cost was approximately US$500 million, shared equally by China and Pakistan.

Successor to the Sabre II Project

The J-17 project was commenced after China and Pakistan abandoned the Sabre II Project based on the F-7 when the third partner, Grumman Aerospace Corporation, pulled out in 1991 following the political fallout from the Tiananmen Square protests in China in 1989.

The JF-17 project, being an altogether new project not based on the F-7, did not originate from the Sabre II project, but it was the successor to the Sabre II project.

Launch of the FC-1/Super-7 Project

After the abandonment of the Sabre II Project, CAC continued further independent studies into modifying the F-7 by providing low-level funding from its own resources.

In 1991, China launched a project for the modification of the F-7 and re-branded it as the "FC-1" (local designation) or "Super-7" (for export). The F-7 was further modified with the delta wings of the F-7 replaced by new wings of cropped-delta planform, featuring a pair of hardpoints on the wing-tips and leading edge root extensions blending the wings, side-mounted air intakes and fuselage.

Requiring a more capable and modern fighter to replace its fleet of F-7P, A-5C and Mirage III/V, the PAF high command debated joining the Super 7/FC-1 project. The PAF informed the Chinese that it would only be willing to join the FC-1/Super-7 project if was based on a completely new design and not on the F-7. The Chinese agreed to this proposal.

In 1995, memorandum of understanding (MoU) was signed between Pakistan and China for joint design and development of a new fighter. Pakistan and China worked out the project details over the next few years. In June 1995 it was reported that Mikoyan MAPO had joined CAC on the project to provide design support, believed to be using experience from their "Izdeliye 33" (English: "Project 33") design, a small single-engine fighter similar to the FC-1/Super 7. However, there is no evidence to substantiate this claim.

In October 1995 it was reported that Pakistan was to select a Western company by the end of the year which would provide and integrate the avionics for FC-1, which was expected to go into production by 1999. The avionics were stated to include radar, INS, HUD and MFD. Competing for the contracts were Thomson-CSF with a variant of the RDY radar, Sagem with avionics similar to those used in the ROSE upgrade programme and GEC-Marconi with the new Blue Hawk radar, but FIAR (now SELEX Galileo) was expected to win the radar contract with the Grifo S7 because the PAF had already upgraded F-7 and Mirage III fighters with the Grifo 7 and Grifo M3 radars.

After a period of little activity, a letter of intent (LOI) covering airframe development was signed in Beijing by Pakistan and China in mid-February 1998. Russia's Klimov was reported to be offering a variant of the RD-33 turbofan engine to power the fighter and a mock-up of the cockpit was put on display at the Singapore air show.

In June 1999 the contract to co-develop and produce the Chengdu FC-1/Super 7 was signed during a visit to Beijing by then Prime Minister of Pakistan Nawaz Sharif and Chinese premier Zhu Rongji. The project was to be a 50-50 partnership with the air forces of both Pakistan and China being committed to ordering the fighter. Avionics suites were being proposed by FIAR and Thomson-CSF, based on the Grifo S7 and RC400 radars respectively, after GEC-Marconi had abandoned the bidding to supply an integrated avionics suite including INS, MFD, HUD and mission computer, despite previously hoping to use the PAF's Super 7 to launch its new Blue Hawk radar.[24] Design work progressed very slowly over the next 18 months due to sanctions, placed on Pakistan after the country's May 1998 nuclear tests, preventing delivery of the advanced Western avionics systems to the PAF.

In early 2001, however, a major decision was taken by the PAF to de-couple the platform (airframe) from the avionics systems, enabling design work on the aircraft to continue. An added advantage would be that as the platform was developed, any new avionics requirements by the PAF could easily be catered for, not easily possible had the aircraft been designed for late-1990s era avionics. Prototype production began in September 2002 and a full size mock-up of the FC-1/Super 7 was displayed at Airshow China in November 2002.[25] The first batch of Klimov RD-93 turbofan engines that would power the prototypes was also delivered in 2002.

It has been reported by a Chinese source that use of modern computer aided design (CAD) software, likely the French CATIA package, shortened the design phase of the JF-17 as well as the dual-seat model of the Chengdu J-10.

Flight testing and re-design - FC-1/JF-17

The first prototype, PT-01, was rolled out on 31 May 2003 and transferred to the Chengdu Flight Test Centre by June 2003 to be prepared for the maiden flight. This was initially planned to take place in June but was delayed due to concerns about the SARS outbreak. The designation Super-7 was replaced by "JF-17" (Joint Fighter-17) at some point during this period. Low speed taxiing trials began at Wenjiang Airport in Chengdu on 27 June 2003. The maiden flight took place in late August 2003, but the actual date is unclear. Some sources report it took place on 24 August 2003 and lasted 17 minutes, others stating it occurred on 25 August 2003 (the first of two test flights that day) and lasted 8 minutes. However the 'official' maiden flight of the prototype took place on either 2 September or 3 September 2003, the prototype being marked with the new Pakistan Air Force designation JF-17. In late March 2004 it was reported that CAC had made around 20 test-flights of the first prototype. On 7 April 2004 the PAF's first test pilots, Sqn Ldr Rashid Habib and Sqn Ldr Mohammad Ehsan ul-Haq, flew the PT-01 for the first time. The maiden flight of the third prototype, PT-03, took place two days later on 9 April 2004. In March 2004 it was reported that Pakistan was now planning to induct around 200 aircraft.

In September 2005 it was reported that flaws in the design had began to surface after the first test flight in 2003, leading to work on design changes being started by Chengdu Aircraft Design Institute (CADI) in 2004. It was believed that the air intakes were being re-designed due to excessive amounts of smoke being emitted by the Klimov RD-93 engine and test-pilot reports of control problems had resulted in changes being made to the wing leading edge root extensions (strakes). It was also stated by CAC that the size of the vertical tail fin was being increased to house an expanded electronic warfare equipment bay at the tip of the fin. The re-designed aircraft was reported to have a maximum take-off weight slightly above the original 12,400 kg (27,300 lb) and a model was put on display at the Aviation Expo 2005 event in Beijing. It was planned that the re-designed prototypes would incorporate Chinese avionics suites, which would later be replaced by the PAF's selected Western suite. As a result of the changes the first deliveries to the PAF were postponed from late 2005 to 2007. Test flights of the original flying prototypes, 01 and 03, were continuing. At this stage Pakistan was evaluating British, French and Italian avionics suites, the winner of which was expected to be finalised in 2006

The fourth prototype and the first to incorporate the design changes, PT-04, was rolled out in a ceremony by CAC in mid-April 2006. On 28 April 2006, PT-04 flew for the first time in a test flight lasting 16 minutes and announced by Chinese news agency Xinhua from Wenjiang airport in Chengdu. Pictures released by CAC gave details of the design changes, which included re-designed air intakes, larger leading edge root extensions (LERX), longer ventral fins underneath the rear of the fuselage and a taller vertical stabiliser fin, with lower angle of sweep and rectangular electronic warfare equipment housing at the tip.

The modifications to the air intakes replaced the conventional intake ramps, whose function is to divert turbulent boundary layer airflow away from the inlet and prevent it entering the engine, with a "diverterless supersonic inlet" (DSI) design very similar to that of the Lockheed Martin F-35 Lightning II. The DSI design uses a combination of forward-swept inlet cowls and a three-dimensional compression surface, referred to as a "bump" due to its shape, to divert the boundary layer airflow away from the intake at high sub-sonic through to supersonic speeds. According to Lockheed Martin, the DSI design prevents the majority of boundary layer air from entering the engine at speeds up to Mach 2, reduces weight by removing the need for complex mechanical intake mechanisms and is more stealthy than a conventional intake.Work on the DSI was started in 1999 with the aim of improving aircraft performance and took almost two years, during which a number of models underwent wind tunnel tests at different speed regimes. It was found that the DSI gave high performance, high total pressure recovery, low integrated distortion and good engine/intake matching.

For the avionics and weapons qualification phase of the flight testing, PT-04 was fitted with a 4th generation avionics suite that incorporates sensor fusion, electronic warfare suite, enhanced man-machine interface, Digital Electronic Engine Control (DEEC) for the RD-93 turbofan engine, FBW flight control, day/night precision surface attack capability and multi-mode pulse doppler radar for beyond visual range air-to-air attack capability, making the aircraft a modern multi-role fighter. A sixth prototype, PT-06, first flew on 10 September 2006

Design
Airframe and cockpit

The airframe is of semi-monocoque structure, constructed primarily of aluminium alloys, although plans are in place to reduce weight by increasing the use of composite materials. High strength steel and titanium alloys are partially adopted in some critical areas. The airframe is designed for a service life of 4,000 flight hours, or 25 years, the first overhaul being due at 1,200 flight hours.

The mid-mounted wings are of cropped-delta planform. Near the wing root are convex strakes, also called leading edge root extensions, which generate a vortex that has the effect of providing more lift to the wing at high angles of attack encountered during combat manoeuvres. A conventional tri-plane empennage arrangement is incorporated, with all-moving stabilator tail-planes, single vertical stabiliser fin and rudder. Twin ventral fins are located underneath the rear of the fuselage. The flight control surfaces are operated by a computerised flight control system (see aircraft avionics), which also adjusts the slats/flaps for improved manoeuvring. Up to 3,629 kg (8,000 lb) of ordnance, equipment and fuel can be mounted on the seven hardpoints; two on the wing-tips, four under the wings and 1 under the fuselage.

The retractable undercarriage is of tricycle arrangement, with a single steerable nose-wheel that under the cockpit between the air intakes and two main gear wheels mounted under the fuselage, between the wings. The hydraulic brakes have an automatic anti-skid system. The nosewheel retracts rearwards into the fuselage and the main gear wheels retract upwards into the engine intake trunks.

Two bifurcated air inlets, one on either side of the fuselage behind and below the cockpit, provide the engine's air supply. The position and shape of the inlets is designed to give the required airflow to the jet engine during manoeuvres involving high angles of attack. A diverterless supersonic inlet (DSI) design is used to separate and prevent boundary layer airflow entering the inlet.

The aircraft cockpit is covered by a transparent acrylic canopy designed to give the pilot a good all-round field of view. A centre stick is used by the pilot to control the aircraft in pitch and roll while rudder pedals control the aircraft's yaw motion (see flight dynamics). A throttle stick to control the engine throttle setting is located to the left of the pilot. The cockpit incorporates "hands on throttle and stick" (HOTAS) controls to allow operation of all essential aircraft systems, especially combat-related systems such as radar and weaponry, without the pilot having to remove his hands from the controls. The pilot sits on a zero-zero capable ejection seat;[6] either the Martin-Baker Mk-16LE, which will be used on Pakistan Air Force fighters,or the Chinese TY-5B also fitted to the Chengdu J-10.

A mock-up showing the entire cockpit, including banks of switches and instruments to the left and right of the pilot.

A mock-up of the initial cockpit design which incorporated two CRT displays and several analogue instruments

Another view of the initial cockpit mock-up.

The glass cockpit of the JF-17, as shown by a JF-17 simulator on display at the MAKS 2007 air show.

The three multi-function displays in different modes.

Avionics

Aircraft avionics

The software written for the JF-17's avionics totals more than one million lines of instructions, incorporating the concept of open architecture. Rather than using the Ada programming language, which is optimised for military applications, the software is written using the popular civilian C++ programming language to better utilise the large number of civilian software programmers available. Avionics equipping the JF-17 prototypes used the Motorola 88000 microprocessor, which can be changed to other microprocessors of the same class. The redesigned PT-04 prototype JF-17 had more advanced avionics than its predecessors, which are included on the production version of the aircraft.

The aircraft's glass cockpit incorporates an Electronic Flight Instrument System (EFIS) and a wide-angle holographic Head-Up Display (HUD), which has a minimum total field of view of 25 degrees. The EFIS is made up of three colour multi-function displays (MFD) providing basic flight information, tactical information and information on the engine, fuel, electrical, hydraulics, flight control and environment control systems. The HUD and MFD are "smart", meaning they can be configured by the pilot to show any of the available information. Each MFD is 20.3 cm (8 in) wide and 30.5 cm (12 in) tall, arranged side-by-side in a portrait orientation (height greater than width). The central MFD is placed lower down to accommodate an up-front control panel (UFCP) between it and the HUD

The People's Liberation Army Air Force (PLAAF) experienced problems with the HUDs of its Russian designed combat aircraft, these tended to fog up due to deployment in humid sub-tropical and tropical zones. The Chinese HUD fitted to the JF-17 was developed to ensure this problem would not occur when deployed in any environment. Western HUDs can be incorporated directly onto the aircraft, if desired by the user, with little effort due to the modular avionics design and the adoption of the MIL-STD-1553B databus architecture. Information from the onboard radar can be displayed on the head-down multi-function displays or projected onto the HUD, the latter feature believed to have been inspired by the HUDs of Russian aircraft. This enables the pilot to keep his eyes focused at infinity so that he can simultaneously view radar images and monitor the airspace around him, without having to re-focus his eyes. Monochrome images from electro-optical navigation/targeting pods carried by JF-17 can also be projected onto the HUD.

The aircraft has a composite flight control system (FCS), comprising conventional controls with stability augmentation in the yaw and roll axis and a digital fly-by-wire (FBW) system in the pitch axis. The leading edge slats/flaps and trailing edge flaps are adjusted by the flight control system automatically during manoeuvring to increase turning performance. Some sources state that the system has been upgraded to provide fly-by-wire flight control in the roll and yaw axis also, the serial production aircraft having a digital quadruplex (quad-redundant) FBW system in the pitch axis and duplex (dual-redundant) FBW system in the roll and yaw axis.
The avionics also include a health and usage monitoring system (HUMS). Automatic test equipment is supplied by Teradyne

Tactical avionics

The communication systems comprise two VHF/UHF radios, one of them having capacity for data linking. The data link can be used to exchange data with ground control centres, AWACS/AEW aircraft and other combat aircraft also equipped with compatible data links. The ability to data link with other "nodes" such as aircraft and ground stations allows JF-17 to become part of a network, improving the situational awareness of the pilot as well as other entities in the network (see network-centric warfare).

The JF-17 has a defensive aids system (DAS) made up of various integrated sub-systems. A radar warning receiver (RWR) gives data such as direction and proximity of enemy radars to the pilot and electronic warfare (EW) suite, housed in a fairing at the tip of the tail fin for greater coverage, that interferes with enemy radars. The EW suite is also linked to a missile approach warning (MAW) system to help it defend against radar-guided missiles. The MAW system uses several optical sensors mounted on the airframe (two of which can be seen at the base of the vertical stabiliser) that detect the rocket motors of missiles and gives 360 degree coverage. Data collected by the MAW system, such as direction of inbound missiles and the time to impact (TTI), is also shown on the cockpit displays and HUD to warn the pilot. A counter-measures dispensing system releases decoy flares and chaff to help the aircraft evade enemy radars and missiles trying to track and destroy the aircraft. The DAS systems will also be enhanced by integration of a self-protection radar jamming pod which will be carried externally on one of the aircraft's hardpoints.

The first 42 production aircraft currently being delivered to the Pakistan Air Force are equipped with the NRIET KLJ-7 radar, a smaller variant of the KLJ-10 radar fitted to the Chengdu J-10, developed by China's Nanjing Research Institute of Electronic Technology (NRIET). Its multiple modes allow surveillance and simultaneous engagement of multiple air, ground and sea targets, of which a total of 40 can be managed. Using the track-while-scan (TWS) mode, the radar can track up to 10 targets at beyond visual range (BVR) and engage 2 of them simultaneously with radar homing air-to-air missiles. The operation range for targets with a radar cross-section (RCS) of 5 m2 is stated to be ≥105 km in look-up mode and ≥85 km in look-down mode.

It is known that a helmet-mounted sights/display (HMS/D) system will be installed on the JF-17, although the exact type is yet to be confirmed. This system assists in targeting enemy aircraft by projecting targeting information onto the pilot's visor and tracking the movements of his head/eyes. A Chinese HMD is stated to be available for installation on the fighter. Also to be integrated is a FLIR (Forward Looking Infra-Red) pod for low-level navigation in low visibility and IRST (Infra-Red Search and Track) system for passive monitoring and targeting of enemy aircraft.

A day/night laser designator targeting pod will be integrated with the aircraft's avionics and carried externally on one of the hardpoints for guiding laser-guided munitions. An extra hardpoint may be added under the starboard air intake, opposite the cannon, for mounting such pods. No specific targeting pod has been selected, but a Chinese system such as the FILAT (Forward-looking Infra-red Laser Attack Targeting) pod may be integrated if a suitable Western system is not available. To reduce costs associated with buying large numbers of targeting pods, during strike missions the aircraft's tactical data-link will be used to transmit targeting data to other aircraft not equipped with targeting pods.

Propulsion and fuel system

The JF-17 is powered by a single Russian Klimov RD-93 turbofan engine, which is a variant of the RD-33 engine used on the Mig-29 fighter. The turbofan engine gives more thrust and significantly lower specific fuel consumption than the turbojet engines fitted to older combat aircraft being replaced by the JF-17. The advantages of using only one engine are that both maintenance time and cost are significantly lower than twin-engined fighters. A thrust-to-weight ratio of 0.99 can be achieved, with full internal fuel tanks and no external payload. The engine's air supply is provided by two bifurcated air inlets (see airframe section).

The Guizhou Aero Engine Group of China has been developing a new turbofan engine, the WS-13 Taishan, since the year 2000 to replace the Klimov RD-93. It is believed to be based on the Klimov RD-33 but incorporates many new technologies to boost performance and reliability. Thrust output of 80-86.36 kN (19,391 lb), life span of 2,200 hours and thrust to weight ratio of 7.8 are expected. An improved version of the WS-13 developing a thrust of around 100 kN (22,450 lb) is also reportedly under development.

The fuel system comprises internal fuel tanks located in the wings and fuselage, with capacity for 2330 kg (5,130 lb) of fuel, that are refuelled through a single point pressure refuelling system (see turbine fuel systems). Internal fuel storage can be supplemented by external fuel tanks. One 800 litre droptank can be mounted on the aircraft's centerline hardpoint under the fuselage and two 800 litre or 1100 litre droptanks can be mounted on the two inboard under-wing hardpoints. The fuel system is also compatible with in-flight refuelling (IFR), allowing the aircraft to take on fuel from a tanker aircraft when an IFR probe is installed and increasing its range and loitering time significantly. All production aircraft for the Pakistan Air Force are to be fitted with retractable IFR probes.

Weaponry

JF17 in 2010 with a display of weapons

A model of the JF-17, armed with six Chinese air-to-air missiles, on display at a defence exhibition. The larger missiles mounted inboard are medium range SD-10s, the four smaller ones being short range PL-5Es.

JF-17 can be armed with up to 3,629 kg (8,000 lb) of air-to-air and air-to-ground ordnance, as well as other equipment, mounted externally on the aircraft's seven hardpoints. One hardpoint is located under the fuselage between the main landing gear, two are underneath each wing and one at each wing-tip. All 7 hardpoints communicate via a MIL-STD-1760 data-bus architecture with the Stores Management System, which is stated to be capable of integration with weaponry of any origin. Internal armament comprises one 23 mm GSh-23-2 twin-barrel cannon mounted under the port side air intake, which can be replaced with a 30 mm GSh-30-2 twin-barrel cannon.

A model of the JF-17, armed with six Chinese air-to-air missiles, on display at a defence exhibition. The larger missiles mounted inboard are medium range SD-10s, the four smaller ones being short range PL-5Es.

The wing-tip hardpoints will normally be occupied by short range infra-red homing air-to-air missiles, while many combinations of various ordnance and equipment (including avionics such as targeting pods) can be carried on the under-wing and under-fuselage hardpoints. Under-wing hardpoints can be fitted with multiple ejector racks, allowing each hardpoint to carry two 500 lb (241 kg) unguided or laser-guided bombs (Mk.82 or GBU-12). It is currently unknown if multiple ejector racks can be used for other ordnance such as beyond visual range air-to-air missiles. The under-fuselage and inboard under-wing hardpoints are plumbed, enabling them to carry droptanks of various sizes for extra fuel (see propulsion and fuel system).

Active radar homing beyond visual range (BVR) air-to-air missiles can be deployed once integrated with the on-board radar and data-link for mid-course updates. The Chinese PL-12/SD-10 is expected to be the aircraft's primary BVR air-to-air weapon, although this may change if radars of other origin are fitted. Short range infra-red homing missiles currently integrated include the Chinese PL-5E and PL-9C, as well as the AIM-9L. The PAF is also seeking to arm the JF-17 with a modern fifth generation close-combat missile such as the IRIS-T or A-darter. These will be integrated with the helmet mounted sights/display (HMS/D) as well as the radar for targeting.

Unguided air-to-ground weaponry includes rocket pods, gravity bombs of various sizes and anti-runway munitions such as the Matra Durandal. Precision-guided munitions (PGM) such as laser-guided bombs and satellite-guided bombs, as well as other guided weapons such as anti-ship missiles and anti-radiation missiles can also be deployed.

Variants

PT-01, PT-02, PT-03 - single-seat initial prototype variant.
PT-04, PT-05, PT-06 - single-seat final prototype variant, redesigned form of the initial variant
JF-17 / FC-1 - single-seat production variant, based on PT-04 redesign.
Dual-seat variant for training and strike roles. Under development, designation unknown

Specifications (JF-17/FC-1)

General characteristics
Crew: 1
Length: 14.0 m (45.9 ft)
Wingspan: 9.45 m (including 2 wingtip missiles) (31 ft)
Height: 4.77 m (15 ft 8 in)
Wing area: 24.4 m² (263 ft²)
Empty weight: 6,411 kg (14,134 lb)
Loaded weight: 9,100 kg including 2× wing-tip mounted air-to-air missiles (20,062 lb)
Max takeoff weight: 12,700 kg (28,000 lb)
Powerplant: 1× Klimov RD-93 turbofan
Dry thrust: 49.4 kN (11,106 lbf)
Thrust with afterburner: 84.4 kN (18,973 lbf)
G-limit: +8.5 g
Internal Fuel Capacity: 2300 kg (5,130 lb)
Performance
Maximum speed: Mach 1.8 (1,191 knots, 2,205 kph)
Combat radius: 1,352 km (840 mi)
Ferry range: 3,000 km (2,175 mi)
Service ceiling: 16,700 m (54,790 ft)
Thrust/weight: 0.99
Armament
Guns: 1× 23 mm GSh-23-2 twin-barrel cannon (can be replaced with 30 mm GSh-30-2)
Hardpoints: 7 in total (4× under-wing, 2× wing-tip, 1× under-fuselage) with a capacity of 3,629 kg (8,000 lb) external fuel and ordnance
Rockets: 57 mm, 90 mm unguided rocket pods
Missiles:
Air-to-air missiles:
Short range: AIM-9L/M, PL-5E, PL-9C
Beyond visual range: PL-12 / SD-10
Air-to-surface missiles:
Anti-radiation missiles : MAR-1
Anti-ship missiles: AM-39 Exocet
Cruise missiles: Ra'ad ALCM
Bombs:
Unguided bombs:
Mk-82, Mk-84 general purpose bombs
Matra Durandal anti-runway bomb
CBU-100/Mk-20 Rockeye anti-armour cluster bomb
Precision guided munitions (PGM):
GBU-10, GBU-12, LT-2 laser-guided bombs
H-2, H-4 electro-optically guided,[7] LS-6 satellite-guided glide bombs
Satellite-guided bombs
Others:
Up to 3 external fuel drop tanks (1× under-fuselage 800 litres, 2× under-wing 800/1100 litres each) for extended range/loitering time
Avionics
NRIET KLJ-7 multi-mode fire-control radar
Night vision goggles (NVG) compatible glass cockpit
Helmet Mounted Sights/Display (HMS/D)
Infra-Red Search and Track (IRST)
Externally mounted avionics pods:
Self-protection radar jammer pod
Day/night laser designator targeting pod
Forward Looking Infra-Red (FLIR) pod

30 mm automatic cannon 2A42

2010-07-20T04:39:00.001-07:00

The Shipunov 2A42 is a Soviet/Russian 30 mm automatic cannon. It is built by the Tulamashzavod Joint Stock Company.

The 30 mm 2A42 cannon has a dual feed. One is for HE-T and the other for AP-T rounds. The gunner can select one of two rates of full automatic fire, low at 200 to 300 rds/min and high at 550 rds/min. According to the manufacturer, effective range when engaging ground targets such as light armoured vehicles is 1,500 m while soft-skinned targets can be engaged out to 2,500 m. Air targets can be engaged flying at low altitudes of up to 2,000 m at subsonic speeds and up to a slant range of 2,500 m. In addition to being installed in a two-person turret on the BMP-2 MICV, this gun is also fitted in the BMD-2 airborne combat vehicle, BMD-3 airborne combat vehicle and BTR-90 (or GAZ-5923) (8 × 8) armoured personnel carrier. A small number of these have now entered service. More recently, the 30 mm 2A42 cannon has been installed in a new turret and fitted onto the roof of the BTR-T heavy armoured personnel carrier based on a modified T-54/T-55 MBT chassis. The cannon is also the main armament of BMPT (Tank Support Fighting Vehicle). It is also used for various armament projects from various manufacturers. The design bureau for the 30 mm 2A42 cannon is the KBP Instrument Design Bureau.

Specifications

Barrels: 1
Length: 3,027 mm
Weight: 115 kg
Rate of fire (sustained): 300 r/min
Rate of fire (max): 600 r/min
Armor penetration (60° sloping at 1,000 m): 18 – 25 mm
Muzzle velocity : 880 m/s (AP-T) - 1,120 m/s (APDS)
Effective range
- Light armor: 1,500 m
- Air targets: 3,000 m
- Ground: 2,500 m
Type: Twin feed, gas operated mechanism
Calibre: 30 x 165 mm
Ammunition: APDS, AP-T, HE, HEI, HE-T, HETP-T, TP

Ammunition

The 2A42 fires 30x165 ammunition, a caliber introduced in 1970's in the Soviet Union to replace previous 30mm autocannon cartridges. Other weapons using this size of cartridge case include the 2A38 and 2A72 autocannons for various vehicle, helicopter and air defence applications, as well as numerous single-, dual- and six-barrel naval and air force cannons. The 2A42, 2A38 and 2A72 fire percussion-primed ammunition; the naval and aerial cannons use electrical priming, and therefore their ammunition is not interchangeable with the land-based ammunition types, despite the same cartridge case size.

Originally three basic types of ammunition were developed in the Soviet Union for the land-based weapons: high explosive incendiary, high explosive fragmentation with tracer, and an armour-piercing ballistic capped with tracer. Later a sub-caliber armour piercing round was introduced, and today also countries other than Soviet Union/Russia manufacture 30x165 percussion-primed ammunition.

The main types of ammunition are

Ammunition type 1
Designation: 3UOF8

Type: HEI
Projectile Weight [g]: 389
Bursting charge [g]: 49 g
Muzzle Velocity [m/s]: 960
Description:

A high explosive incendiary round wit A-670M nose fuze.. The fuze produces a 0.15 millisecond delay on impact, and a self-destruct mechanism detonating the projectile after 7.5 to 14.5 seconds of flight (3900–5300 m distance from muzzle).

Ammunition type 2

Designation: 3UOR6
Type: HE-T
Projectile Weight [g]: 385
Bursting charge [g]: 11.5 g
Muzzle Velocity [m/s]: 960
Description:

Nose-fuzed high explosive fragmentation tracer round,utilizing the same A-670M impact/self-destruct fuze as the 3UOF8. Tracer burn time 10 to 14 seconds.

Ammunition type 3

Designation: 3UBR6
Type: APBC-T
Projectile Weight [g]: 400
Bursting charge [g]: none
Muzzle Velocity [m/s]: 970
Description:

Solid shot with blunt penetrator covered by a hollow windshield cap. Tracer burn time 3.5 seconds. Penetration:

20mm thick plate at 60 degree impact, 700 m range

14mm thick plate at 60 degree impact, 1500 m range

18mm thick plate at 60 degree impact, 1500 m range

Ammunition type 4

Designation: 3UBR8
Type: APDS
Projectile Weight [g]: 304
Bursting charge [g]: none
Muzzle Velocity [m/s]: 1120
Description:

A sub-caliber discarding sabot. No tracer. Penetration:

25mm thick plate at 60 degree impact, 1500 m range

Ammunition type 5

Designation: M929
Type: APFSDS-T
Projectile Weight [g]: ??
Bursting charge [g]: none
Muzzle Velocity [m/s]: ??
Description:

A sub-caliber fins-stabilized discarding sabot round with tracer from Belgian Mecar, with tungsten alloy penetrator.[6] Penetration:

55mm steel at 1000m, 45mm at 2000m range.

Platforms

The autocannon has been used since the 1980s on the following platforms:

Infantry Fighting Vehicles
2T Stalker

BMP-2
BMD-2
BMD-3
BTR-90
BTR-T
BMPT
Fahd 280-30

Attack helicopters

Mil Mi-28

Kamov Ka-50
Kamov Ka-52

What is GUN

2010-07-19T11:29:00.000-07:00

In military parlance, a gun is a muzzle or breech-loaded projectile-firing weapon. There are various definitions depending on the nation and branch of service. A "gun" may be distinguished from other firearms in being a crew served weapon such as a howitzer or mortar, as opposed to a small arm like a rifle or pistol, but there are exceptions, such as the USAF's GUU5/P. At one time, land based artillery tubes were called cannon and sea-based naval cannon were called guns. The term "gun" morphed into a generic term for any tube launched projectile firing weapon used by sailors including boarding parties and marines.

In modern parlance, a gun is a projectile weapon using a hollow, tubular barrel with a closed end—the breech—as the means of directing the projectile (as well as other purposes, for example stabilizing the projectile's trajectory, aiming, as an expansion chamber for propellant, etc), and firing in a generally flat trajectory.

The term "gun" has also taken on a more generic meaning, by which it has come to refer to any one of a number of trigger-initiated, hand-held, and hand-directed implements, especially with an extending bore, which thereby resemble the class of weapon in either form or concept. Examples of this usage include staple gun, nail gun, glue gun, grease gun. Occasionally, this tendency is ironically reversed, such as the case of the American M3 submachine gun which carries the nickname "Grease Gun".

Barrel types include rifled—a series of spiraled grooves or angles within the barrel—when the projectile requires an induced spin to stabilize it and smoothbore when the projectile is stabilized by other means or is undesired or unnecessary. Typically, interior barrel diameter and the associated projectile size is a means to identify gun variations. Barrel diameter is reported in several ways. The more conventional measure is reporting the interior diameter of the barrel in decimal fractions of the inch or in millimeters. Some guns—such as shotguns—report the weapon's gauge or—as in some British ordnance—the weight of the weapon's usual projectile.

Types of guns

Military firearms

Long gun

Arquebus

Blunderbuss

Musket

Musketoon

Wall gun

Grenade launcher

Submachine gun

Personal defense weapon

Rifle

Lever action rifle

Bolt action rifle

Assault rifle

Battle rifle

Carbine

Service rifle

Sniper rifle

Shotgun

Combat shotgun

Semi-automatic shotgun

Automatic shotgun

Machine guns

Gatling gun

Minigun

Nordenfelt gun

Metal storm

Mitrailleuse

Submachine gun

Machine pistol

Machine gun

General-purpose machine gun

Light machine gun

Squad automatic weapon

Infantry Automatic Rifle

Medium machine gun

Heavy machine gun

M134 Minigun

Handguns

Handgun

Pistol

Service pistol

Revolver

Service revolver

Machine pistol

Autocannon

Autocannon

Chain gun

Artillery guns

Artillery gun

Cannon

Carronade

Falconet

Field gun

Howitzer

Tank guns

Tank gun

Hunting guns

Elephant gun

Express rifle

Shotgun

Muzzleloader

Breechloader

Guns for training and entertainment

Airsoft gun

BB gun

Paintball gun

Replica gun

Inert gun

Spud gun

Water gun

Nerf gun

G3

2010-07-16T03:24:00.000-07:00

The G3 is a 7.62mm battle rifle developed in the 1950s by the German armament manufacturer Heckler & Koch GmbH (H&K) in collaboration with the Spanish state-owned design and development agency CETME (Centro de Estudios Técnicos de Materiales Especiales).

The origin of this rifle can be traced back to the final years of World War II when Mauser engineers at the Light Weapon Development Group (Abteilung 37) at Oberndorf am Neckar designed the MKb Gerät 06 (Maschinenkarabiner Gerät 06 or "machine carbine instrument 06") prototype assault rifle chambered for the intermediate 7.92x33mm Kurz cartridge, first with the Gerät 06 model using a roller-locked short recoil mechanism originally adapted from the MG 42 machine gun but with a fixed barrel and conventional gas-actuated piston rod. It was realized that with careful attention to the mechanical ratios, the gas system could be omitted. The resultant weapon, the Gerät 06H (the "H" suffix is an abbreviation for halbverriegelt or "half-locked") was assigned the designation StG 45(M) (Sturmgewehr 45(M)) but was not produced in any significant numbers and the war ended before the first production rifles were completed

The German technicians involved in developing the StG 45(M) were taken to work in France at CEAM (Centre d'Etudes et d'Armement de Mulhouse). The StG 45(M) mechanism was modified by Ludwig Vorgrimler and Theodor Löffler at the Mulhouse facility between 1946 and 1949. Three versions were made, chambered in .30 Carbine, 7.92x33mm Kurz as well as the experimental 7.65x35mm French short cartridge developed by Cartoucherie de Valence in 1948. A 7.5x38mm cartridge using a partial aluminium bullet was abandoned in 1947. Löffler's design, designated the Carabine Mitrailleuse Modèle 1950, was retained for trials among 12 different prototypes designed by CEAM, MAC, and MAS. Engaged in the Indochina War and being the second NATO contributor, France canceled the adoption of these new weapons for financial reasons.

In 1950, Vorgrimler moved to Spain where he created the LV-50 rifle chambered for the Kurz cartridge and later, the proprietary 7.92x40mm CETME M53 round.[5] At this point, the rifle was renamed the Modelo 2. The Modelo 2 drew the attention of the West German Border Guards (Bundesgrenzschutz), who sought to re-equip the newly formed national defense forces. Not willing to accept a cartridge outside of the NATO specification, the Germans asked CETME to develop a 7.62x51mm version of the rifle. The resulting CETME Model A was chambered for the 7.62x51mm CETME cartridge which was identical in chamber dimensions but had a reduced-power load compared to the 7.62mm NATO round. Further development of the rifle with input from H&K produced the CETME Model B which received several modifications, including the ability to fire from a closed bolt in both semi-automatic and automatic firing modes, a new perforated sheet metal handguard (the folding bipod had been the foregrip in previous models), improved ergonomics and a slightly longer barrel with a 22 mm rifle grenade launcher guide. In 1958, this rifle was accepted into service with the Spanish Army as the Modelo 58, using the 7.62x51mm CETME round

In 1956, the Bundesgrenzschutz canceled their planned procurement of the CETME rifles, adopting the Belgian-made FN FAL (G1) instead. However, the newly formed West German Army (Bundeswehr) now showed interest and soon purchased a number of CETME rifles (7.62x51mm NATO chambering) for further testing. The CETME, known as the Automatisches Gewehr G3 according to German nomenclature, competed successfully against the Swiss SIG SG 510 (G2) and the American AR-10 (G4) to replace the previously favored G1 rifle. In January 1959, the Bundeswehr officially adopted the CETME proposal. The West German government wanted the G3 rifle to be produced under license in Germany; purchase of the G1 had previously fallen through over FN's refusal to grant such a license. In the case of the G3, the Dutch firm Nederlandse Wapen en Munitiefabriek (NWM) held production and sales rights to the CETME design outside of Spain. To acquire production rights, the West German government offered NWM contracts to supply the Luftwaffe with 20 mm ammunition. Production of the G3 was then assigned to Rheinmetall and H&K. The latter company already had ties to CETME, and had worked to further optimize the CETME rifle for use with the full-power 7.62x51mm NATO cartridge (as opposed to the downloaded CETME variant). In 1969, Rheinmetall gave up production rights to the G3 in exchange for H&K's promise not to bid on MG 3 production. Later in 1977, the West German government ceded ownership of G3 production and sales rights exclusively to H&K

Initial production G3 rifles differed substantially from more recent models; early rifles featured closed-type mechanical flip-up sights (with two apertures), a lightweight folding bipod, a stamped sheet steel handguard, a wooden buttstock (in fixed stock models) or a telescopic metal stock. The weapon was modernized during its service life (among other minor modifications it received new sights, a different flash suppressor, and a synthetic handguard and shoulder stock), resulting in the most recent production models, the G3A3 (with a fixed polymer stock) and the G3A4 (telescoping metal stock). The rifle proved successful in the export market, being adopted by the armed forces of over 40 countries. The G3 was and in some cases continues to be produced under license in: France (MAS), Greece (Hellenic Arms Industry), Iran (Defense Industries Organization), Luxemburg (Luxemburg Defense Technologi ), Mexico, Myanmar, Norway (Kongsberg Våpenfabrikk), Pakistan (Pakistan Ordnance Factories), Portugal (FBP), Saudi Arabia, Sweden (FFV), Thailand, Turkey (MKEK) and the United Kingdom (Royal Ordnance).

Specifications
Weight 4.4 kg (9.7 lb) (G3A3)
4.7 kg (10 lb) (G3A4)
5.54 kg (12.2 lb) with optic (G3SG/1)
4.1 kg (9.0 lb) (G3K)
Length 1,025 mm (40.4 in) (G3A3)
1,025 mm (40.4 in) stock extended / 840 mm (33.1 in) stock collapsed (G3A4)
1,025 mm (40.4 in) (G3SG/1)
895 mm (35.2 in) stock extended / 711 mm (28.0 in) stock collapsed (G3K)
Barrel length 450 mm (17.7 in)
315 mm (12.4 in) (G3K)
Cartridge 7.62x51mm NATO
Action Roller-delayed blowback
Rate of fire 500-600 rounds/min
Muzzle velocity 800 m/s (2,625 ft/s)
Effective range 100–400 m sight adjustments
Feed system 20-round detachable box and 50-round drum magazine
Sights Rear: rotary diopter; front: hooded post.
Produced 1964–present
Variants See Variants
Type Battle rifle
Place of origin West Germany

Variants

G3: Original model based on the CETME Modelo B.
G3A1: G3 with a single position, collapsible stock. This design was chosen after earlier experimentation with a ventrally-folding stock. Excessive recoil caused the latter to be dropped from consideration.
G3A2: G3 with new rotating drum rear sight.
G3A3: The most well known version. Drum sights, a fixed plastic buttstock, and a plastic handguard that does not contact the barrel. The handguard came in a slim, ventilated version and a wide version. The latter allows for the attachment of a bipod.
G3A3A1: This is a version of the G3A3 with an ambidextrous trigger group and brass deflector. This is an official German Army designation, not a HK factory one.
G3A4: The G3A4 uses drum sights and a single position, collapsible stock. This rifle could also be issued with a scope with the nomenclature G3A4ZF. The ZF stands for Zielfernrohr or "Telescope".
G3A4A1: This is a variant of the G3A4 with an ambidextrous trigger group and brass deflector. This is an official German Army designation, not a HK factory one.
G3KA4: Smallest of the line, it is a Karabiner, or carbine version of the G3. It features drum sights, a retractable stock, and a 315 mm (12.4 in) barrel.
G3KA4A1: Variant of the G3KA4 with an ambidextrous trigger group and brass deflector. This is an official German Army designation, not a HK factory one.
G3A5: HK assigned model number for the HK-made Danish version of the G3A3. It differs in that it has a silent bolt-closure device. In Danish service it is known as the Gv M/66. The Gv M/66 was originally intended for use with optics as a designated marksman rifle, while the rest of the squad were issued M1 Garands.
G3A6: HK assigned model number for the Iranian-made version of the G3A3.
G3A7: HK assigned model number for the Turkish-made version of the G3A3.
HSG1: HK assigned model number for the Luxembourg- made version of G3A3.

Other military variants and derivatives

Gv M/75: Variant leased from the German Bundeswehr / German government by the Danish government to replace the aging M1 Garands. Originally manufactured by either Rheinmetall or HK for the German Bundeswehr. The Gv M/75 rifles are basically G3's with the old style straight cocking tube as opposed to the later FS (Freischwinger) variant. Semi-automatic normally, though could be converted to fully automatic fire by changing the safety lever. This is done without tools.
AG-3: Norwegian G3A5 variant produced by Kongsberg Våpenfabrikk. A total of 253,497 units were produced for the Norwegian Armed Forces from 1967 to 1974. The Norwegian AG-3 differs from the original G3; it has a buttstock that is approx. 2 cm longer, the bolt carrier has a serrated thumb groove to aid in silent bolt closure, it features an all-metal cocking handle and a different bayonet mount. On April 11, 2007, it was announced that the AG-3 would be replaced by the Heckler & Koch HK416, in all military branches except for certain groups of the Home Guard. A Latvian soldier providing security for coalition forces with a Swedish-made Ak4 in Iraq, 2006.
AG-3F1: An AG-3 with a retractable stock as on G3A4. Produced by Kongsberg Våpenfabrikk. A retractable stock was required by certain groups of soldiers within the Norwegian Armed Forces, primarily vehicle crews with limited space inside, particularly where a quick disembarkment from such a vehicle is required. All versions of the AG-3 have the ability to attach a 40 mm HK79 grenade launcher.
AG-3F2: An improvement of the AG-3F1, featuring Picatinny rails on the receiver as well as the foregrip.
Ak 4: Swedish-made version of the G3A3. The rifles were manufactured from 1965 to 1970 by both Carl Gustafs Stads Gevärsfabrik and Husqvarna Vapenfabrik and from 1970 until the end of production in 1985 - exclusively by Gevärsfabrik in Eskilstuna. Also produced with a Hensoldt 4x24 telescopic sight mounted via a HK claw mount, known as the Ak 4OR(No longer issued) and the Ak 4B variant, where the iron sights have been removed, and replaced with a Aimpoint CS red-dot reflex sight mounted on a permanently mounted picatinny rail and an increased rate of fire. All Ak 4s are adapted to mount the M203 grenade launcher. Sweden has supplied Ak4s to Estonia, Latvia and Lithuania.
DIO G3 Bullpup: Iranian bullpup variant of the G3.
G3A7A1: Turkish-made variant of the G3A4.
G3P4: Pakistan Ordnance Factory designation for license produced G3A4 rifles

Specialized G3 types

G3TGS: This is simply a G3 with a 40 mm HK79 under-barrel grenade launcher. TGS stands for Tragbares Granat System ("portable grenade system").
G3A3ZF: This is a rifle issued with a scope bracket and a scope. The ZF stands for Zielfernrohr or "telescopic sight".
G3SG/1: An accurized variant of the G3. The "SG" stands for Scharfschützengewehr, or "sharpshooting rifle". The rifles were individually selected from the production line for their accuracy and then modified. A Zeiss 1.5-6x variable power telescopic sight was added using a HK claw mount attached to the receiver. The stock was extended slightly compared to the standard G3 fixed stock and comes with a heavy, dual-stage buffer and adjustable cheek rest. A special set trigger group was added for a crisp trigger pull of 1 lb. Automatic fire was retained.
MSG3: A variant featuring the newer scope mount that is found on only a few of the Heckler & Koch rifles, as compared to the more conventional claw mounts, though the claw mounting points remain on the receiver. This newer scope mount does not allow the use of the open sights with the mount in place, as is the case with the more conventional claw mount.
PSG-1: A free-floating barrel semi-auto only version of the G3 with numerous other upgrades and such to meet the necessities of police sniper units. This rifle is famous for its accuracy and comfortability, but infamous for its price and inability to be deployed because some upgrades made the rifle too fragile.
MSG-90: A somewhat cheaper version of the PSG-1 modified for military applications.

Law enforcement and civilian models

HK41: The HK41 is a semi-automatic version of the G3 that was marketed to law-enforcement and civilian reservists (the prefix number 4 in HK's two-digit number system technically stands for "para-military rifle"). There were two versions, one differing from the G3 by being fitted with a semiautomatic-only trigger pack, the other using a different design of trigger pack, like that of the later HK91. The first version could easily be converted to a full-automatic weapon by swapping out several parts. Limited sales at home and US import restrictions and firearms regulations led this weapon to be dropped from HK's product line quickly and it was replaced by the HK91.
HK91: The HK91 is a semi-automatic version of the G3 similar to the HK41, also marketed to civilians. However, in order to comply with US firearm regulations a number of modifications to the HK91 were made that do not appear on the first pattern HK41. Internal parts that could allow fully automatic fire were removed. A shelf was welded onto the receiver where the push-pin of the trigger pack would normally go, to prevent installation of a fully automatic trigger pack. This did not allow the use of the paddle style magazine release and so the magazine release button on the right side of the magazine well must be used instead. This was considered awkward by many owners. It is otherwise identical to the G3A3/A4. Importation into the United States began in 1974 and ceased in 1989, with some 48,000 rifles being imported.
HK911: The HK911 was an HK91A2 with the flash hider removed and the receiver re-stamped with an extra 1 to comply with the US importation ban of 1989. The new designation theoretically made it legally immune to the Import Ban, as no "HK911" rifles were mentioned on the list of banned guns. However, the later banning of several "paramilitary" features on the HK911 made it illegal.
SR9: These variants of the HK91ZF were created to comply with the Semi-Auto Import Ban of 1989, which included all variants of the HK91. They differed from the HK91 in that they had their flash hiders removed and featured a smooth forend that lacked the bipod attachment point. The SR9 series were banned from importation to the United States by President Clinton in 1997 because they could accept standard-capacity magazines. The SR9 was an HK91A2ZF with the pistol grip and buttstock replaced with a one-piece thumbhole stock.

SR9 (T): The (T), or "Target", model was an HK91A2ZF with the trigger replaced with the PSG-1 model, the pistol grip replaced with an ergonomic PSG-1 grip and the buttstock replaced with an MSG90 model.
SR9 (TC): The (TC), ot "Target Competition", model was an HK91A2ZF with the trigger group, pistol grip and buttstock derived from the PSG-1.

G3A1: The terminology used by custom gunsmiths (e.g. Choate) and importers (e.g. Interarms) for weapons with an aftermarket side-folding stock. This is not part of official HK nomenclature.
HK 51: The HK51 is not made by HK, instead being a creation of the American custom after-market. The HK 51 has no real standards but is usually a cut down and modified G3A3 or its semi-automatic clones the HK41 and HK91 and modified to take MP5 furniture and accessories. It is usually fitted with a collapsible stock; 211 mm (8.31 in) barrel; it is 589 mm (23.17 in) in length with the stock retracted and 780 mm (30.72 in) with the stock extended. Originally made by Fleming Firearms.
PTR 91 Series: Additionally, JLD started manufacturing semi-automatic copies of the HK G3 called the PTR 91 in the United States. They used tooling from the FMP arms factory in Portugal to build the rifles.