Armes de fabrication Israelienne

Rappel du premier message :

Citation :

In the mid-70s a group of IAI (Israel Air Industries) engineers and IAF (Israeli Air Force) officers began a new project to develop an ultra modern Israeli fighter aircraft – a project that was supposed to take a quantum leap for aeronautics.

Designed to be the most advanced of its kind in the world by any standards, the Arie (Lion), would give the IAF a reliable option to the advanced US F-15 and F-16 types. Although it has never came through, the Arie became the cornerstone of another future and most ambitious project ever, an Israeli breakthrough to develop and produce the Lavi, the Israeli dream aircraft to outmatch the F-16.


Background

In response to the French embargo forced upon Israel after the Six-day warin 1967, a decision was made to strive for independence in the development of major weapons systems. Israel had already acquired the means to build good copies of the French Mirage, but wanted to be much more than just a clone maker.
The commander of the IAF (1982-1987), Gen. Amos Lapidot: said, “The essence was to create a technological infrastructure to develop and manufacture weapons systems in the three major weapons systems platforms – tanks, aircraft and ships. Behind that concept, were three basic rationales: First, Israel should not, and could not rely on foreign countries very volatile foreign policies. Secondly, the Israeli air force always strives to develop and use new war tactics and strategies, and was in constant need of new equipment to fulfill those operational objectives. Third, a national strategy to promote Israel 's and IAI's state-of-the-art technological accomplishments". This last point doesn't come over so well in English - by implication, these accomplishments would deter aggression, save money on expensive foreign weapon imports and maybe help Israeli exports.


Development

In 1974, an IAI team was set up to begin the Arie project. As no government approval had yet been received to produce it, the program was simply codenamed “R&D project”. Ovadia Harrari, who would later become head of the Lavi program, was to lead that endeavor.
The IAI decided to develop the Arie based on the technological knowhow acquired from the Kfir project, particularly from the Kfir-Canard program – the improved version. In fact, the first proposal which was put on hold by the Air Force, was to develop an aircraft to be named “Super Kfir” – a regular Kfir whose original J79 engine was replaced by an F100 model, the same as in early F-15/F-16s versions. That new engine would substantially increase the Super-Kfir's flying performance. However, due to the Air Force's strict specs requirements, a new draft was called for, in spite of the Kfir/Arie's visual similarities.
Over thirty different configurations were evaluated. The IAI tested several engine models, including the British Rolls- Royce RB-199, which powers the European Tornado aircraft. Soon, the options were reduced to just two. The F-100 single engine plane, or a twin-engine version.
The later, codenamed Light Weight Fighter-4 (LWF-4), was to be powered by two General-Electric F-404 engines as used in the F-18. “Looking at the different designs of the Arie, one can notice that it is an extensively modified Kfir” explains Harrari ,“ the aircraft is visually different, but its roots lay in the Kfir”.
The new future fighter aircraft, which was now codenamed “Hadish” (innovative), could be described as a single seat light fighter, capable of reaching 2.4 Mach speed, a 75,000 ft altitude ceiling, with a 480 km combat radius. Armament: would have been a 30-mm cannon and medium range air-to-air missiles. Avionics would include a radar, a helmet sight and an integral electronic warfare system. In addition, the aircraft would have low optical and radar signatures. Even the US F-15 and F-16 could not match these features at that time.
The outstanding question: An air-to-air fighter, or an air-to-ground attack aircraft?
During its initial design phases, the 1973Yom-Kippur war broke out, and the Israeli Air Force focused its attention on the battle proven air-to-air configuration concept, as air power and air superiority consist basically of air-to-air combat missions. Therefore, about 90 percent of the “Hadish” capabilities would be directed for air-to-air combat.


Technologies and Avionics


The Arie had several technological breakthroughs. It was designed to be the first Israeli aircraft to deploy digital fly-by-wire flight control system (at that time, cutting edge technology). This fly-by-wire concept, permitted the engineers to design an aerodynamically non-stable platform. Hence, they could achieve a small and highly maneuverable aircraft.
In the air-to-air version, to cope with enemy intruder aircraft, and keeping its air-superiority capabilities, the Arie would be equipped with advanced avionics and special ordnance systems: a highly sensitive Israeli radar capable of acquiring low-altitude flying targets. Advanced electro-optical systems would enable the Arie to locate ground targets at night.
Another breakthrough, was the pilot's option to use his helmet mounted sight, easing his combat workload. In the mid-70's these systems were nearly unheard of. It would take another ten years for the helmet mounted sight to become operational in any type of combat aircraft.
The Arie's cockpit resembles to a great extent that of the F-16's early versions. Besides the Head-up Display (HUD), a Monochromatic Display was mounted in the cockpit to display the radar's viewpoint.
The Pilot's view was close to 360º visibility– a life and death factor in air combats. This is now the normal design in both Western and Russian combat aircraft from the F-15 onwards.
The Arie's ordnance would include an improved 30-mm DAPA cannon, assorted air-to-air missiles, iron bombs, and precision guided ordnance. Max. military load is: 7 tons.
Although that aircraft was not meant to be a stealth aircraft, some basic stealth features were studied to give it the option to strike heavily fortified missile zones. This objective was based on the lessons learned during and after the 1973 Yom-Kippur war, when Israeli fighters had to face a huge number of SAMs. The Arie would also be equipped with an advanced Electronic-Warfare system produced by Israel , giving the pilot an early warning signal to lock on to enemy threats and jam them.
Studies were made to drastically reduce its radar signature, making it extremely difficult to be detected by enemy radar. For example, its bomb load was to be stowed inside a conformal ventral capsule, to reduce its radar cross section.


A Paper's Lion

According to the program timetable, the Arie's initial development phase should have been completed by mid 1979. Until then, the IAI would have to complete flight tests, select and define all the contractors.
By that year's end, an initial test flight was scheduled for the first of three prototypes.
By mid 1980, 10 pre-production aircrafts should be completed, with regular production to begin in the following two years. The Air Force should be receiving the first production Arie by the end of 1983. Delivery of 100 aircraft would be completed by the end of 1985.
Meanwhile, the IAF was leaning towards the US aircraft option. Rumors indicated that the USA would finally agree to sell Israel F-15s and F-16s. Finally, a decision was made to order the US aircraft. and scrap the Arie.
In August 1975, the IAF's chief, the (late) Gen. Benny Peled released a document defining the IAF's policy in relation to the Arie project. The document recommended the US F-15s and F-16s. Based on his assessment, the IAF began a procurement program of F-15s to be delivered by 1976. Moreover, it had been determined that the F-16 in principle answered Israel 's operational needs for an air superiority aircraft for the 80s. As a result of intense pressure on the IAF, Gen. Benny Peled decided to respond with a letter on May 10, 1976 , stating the reasons not to progress with the Arie: The US would agree to sell Israel F-16s. It had also been agreed that the US would sell Israel the F-100 engine, and there were not sufficient funds to keep the project moving.
“The fundamental knowledge that led to the development of the Lavi relied on the experience acquired from the “Hadish” and Arie”, says Gen. Lapidot, who created the Lavi project board, and commanded the Israeli Air Force by the time the project was canceled. “It can be definitely stated that the Arie, the Nesher and Kfir programs, added significantly to the development of the Israel Aircraft Industry (IAI), so that when we gave the “go ahead” for the Lavi, we already had a complete infrastructure in place and ready to work. In 1980, we decided to build a smaller version of the Arie. It is not by coincidence that it was named the Lavi. Lavi is a Lion (Arie), although a very much younger and smaller one”

Type Single-seat, multi-role aircraft
Max. speed 2.4 Mach
Max. altitude 75,000 feet
http://www.israeli-weapons.com/weapons/aircraft/arie/Arie.htm

SKYLARK LE

Rafael Sea Spotter

Rafael Blue Sparrow

anti-ballistique
range glaive?

Yakuza a écrit:

anti-ballistique
range glaive?

Ce missile simule le comportement et la trajectoire des missiles syriens ou iraniens type scud D shihab 3 sejil 2....il faut savoir que la France a achete ce missile pour s'en servir en tant que cible a abbatre pour ces anti-missile Aster 30.
les americains affirme que les israeliens peuvent s'en servir pour abbatre des satellites,mais le programme futur a ma conaissance serai qu'israel lance des nano et micro satelittes dans les 3 ans a venir ,nom de code constellatin David.

Voila voila j'espere que j'ai eclairé ta lanterne.

merci

Des Nano satellites ? Glaive tien nous au courant dés que ta des information sur cela s'il te plait Merci d'avance.

Nano je peux deja t'apporté plusieurs informantions sur les nano satellittes futur d'Israel

Citation :

: "ISRAËL VA PRODUIRE DES NANO-SATELLITES A USAGE MILITAIRE QUI VONT PESER QUELQUES DIZAINES DE KILOS
L’Etat hébreu est considéré comme l’un des plus avancés en matière de “mini-satellites”. Contrairement aux satellites “mammouths” américains, qui peuvent peser jusqu’à 25 tonnes, les satellites israéliens mis au point et fabriqués par l’Industrie aérospatiale (IAI) pèsent entre 300 et 400 kg.
JPost : "Actuellement, IAI travaille en outre sur l’élaboration de nano-satellites, qui ne pèseront que quelques dizaines de kilos et seront capables de fournir des services de communications pour les opérations militaires.
“Le monde commence à comprendre que, plus c’est petit, mieux c’est”, déclare Eshed. “Un gros satellite coûte beaucoup d’argent à élaborer, à lancer et à entretenir.”
Et de faire part de son nouveau projet : les satellites “double usage”, qui pourront appartenir en partie à des investisseurs privés israéliens ou étrangers et fournir des services, tant civils que militaires.
Le ministère de la Défense reçoit déjà des images d’ImageSat International, une entreprise internationale, fournisseur commercial d’images haute-résolution de la terre prises par satellite.
S’il faut désormais des investisseurs privés, c’est que les budgets sont serrés : Eshed ne dispose que de quelque 100 millions de dollars, alors que les Etats-Unis, à titre comparatif, en investissent chaque année 50 milliards dans leurs programmes spatiaux".

Israelvalley.com

IAI travaille sur deux type de lancement l'un en coopération avec Rafael et son blue sparrow,l'autre avec un lanceur shavit modifié lancé a partir d'un C-130 et ensuite direction l'espace.

l'université du technion a deja son propre nano satellitte nommé Techsat
je poste un récapitulatif complet sur ce nano-sat
%" border=0]

TechSat/Gurwin-II TechSat/Gurwin-II is a microsatellite, built by students of the Haifa-based Technion (Israel Institute of Technology) with industrial and government support (the S/C is also referred to as TechSat-1B, as well as OSCAR-32 by the AMSAT community; the COSPAR ID is: 1998-043-D). TechSat is a microsatellite family of Asher Space Research Institute (ASRI) of Technion. As a university, Technion is involved in the development of space-qualified systems based on advanced and innovative technologies. The microsatellite is named in honor of Joseph and Rosalind Gurwin whose long-term support for space research at Technion enabled the TechSat mission. 1) 2) 3) The TechSat development started in 1993. TechSat-1a, a technology demonstration microsatellite (50 kg), was launched March 23, 1995 on a Russian Start launcher (a newly converted Russian intercontinental ballistic missile) - unfortunately, this mission experienced a launch failure. Spacecraft: The TechSat/Gurwin-II satellite is of cubic shape with a size of 445 mm x 445 mm x 445 mm. The platform is three-axis stabilized, using a momentum wheel and three magnetorquers as actuators, and a three-axis magnetometer as attitude sensor. All attitude instruments have a total power consumption of about 3 W. The power consumption for all housekeeping functions is less than 10 W (including transmitters, receivers, on-board computer, and power conditioning. The satellite attitude history, based on the magnetometer telemetry processed both by the onboard and ground station Kalman filters, was statistically analyzed, to summarize the long-term performance of the attitude control system. The analysis made it evident, that throughout the most part of the flight, the magnetic control provided the 3-axis stabilization of the satellite with nadir-pointing accuracy of about 2º-2.5º. The solar cells employ thin-film photovoltaic cell technology (developed in Russia); they are mounted on four sides of the six outer aluminum panels. A NiCd battery is provided for eclipse operations. The fifth panel, pointing toward Earth, includes antennas, the retroreflector, the UV spectro radiometer (OM-2) and an imaging camera. When 3-axis stabilized, the satellite would have its sixth panel unlit; it is not exposed to the sun and therefore does not include any solar cells. The structure plays a major role in the thermal design. The heat flows from the solar illuminated panels to all parts of the structure that are used as radiators. The S/C mass is 48 kg, the total payload mass is 6.6 kg, power = 20 W. The S/C design life is one year. 4) Figure 1: The TechSat/Gurwin-II satellite and its components (image credit: ASRI/Technion) Launch: The Earth-pointing satellite was launched as a secondary payload on July 10, 1998. A Russian Zenit-2 vehicle carried the Resurs-O1-4 satellite (primary payload) and five piggyback payloads (TMSAT, TechSat/Gurwin-II, FASat-Bravo, and SAFIR-2) from the Baikonur Cosmodrome into orbit. RF communications: Communication is realized via receive and transmit antennas. Three uplinks in the 145 MHz VHF band (2 m), three uplinks in the 1270 MHz L-band (23 cm), and one downlink in the 435 MHz UHF-band (70 cm). Data is transmitted at two available rates: 1200 bit/s and 9600 bit/s. At 1200 bit/s the carrier modulation is BPSK (downlink) and FM (uplink). At 9600 bit/s the carrier modulation is FM (downlink & uplink). Satellite operations are conducted from a ground station at Technion. The S/C features a digital store and forward multi-user system, compatible with existing store and forward facilities already in use on microsatellites (use by the international amateur radio electronic community). 5) 6) Orbit: Sun-synchronous circular orbit, altitude = 820 km, inclination = 98.8º, period =101 min, local time of equator crossing is at 10 AM in descending node. Figure 2: Illustration of the TechSat/Gurwin-II spacecraft (image credit: ASRI/Technion) Mission status: TechSat/Gurwin-II is operating nominally as of August 2008 (> 10 years after launch - surpassing many times its design life). All its subsystems (attitude, communication, computer, etc.) and some of testing devices are still functioning. Although the operational status of the power system is normal, a further reduction of charging current from the solar panels would bring about a system non-stability, and a subsequent failure. The satellite is also available for Amateur radio services. Lately, the satellite is providing services in two interchangeable modes of operation: 1) amateur service, or 2) space experiments, over the TM downlink. 7) The mission duration and design flexibility allowed for more experiments to be conducted than originally planned. Additional investigations of significance were testing of the new attitude control algorithms and evaluation of the solar panel deterioration. ACS (Attitude Control System): For most of the time the TechSat attitude control system operated in a standard, 3-axis-stabilization mode. The checks of the satellite's attitude have been done periodically. An experiment was staged onboard the TechSat of a purely magnetic attitude control, able to provide 3-axis stabilization, given a magnetometer as the only sensor, and magnetic torquers as the only actuators, with two different solutions to the problem, namely `Linear Quadratic Regulator' and `No Wheel' controllers, developed, respectively, at Cornell University (Ithaca, NY, USA) and at ASRI/Technion. 9) 10) • In late 2005, after more than seven years in space, TechSat/Gurwin-II is still working and providing valuable information, showing no significant degradation. 11) • One of the TechSat mission goals was to carry out long-term experiments, and to compare the actual in-flight parameters of the onboard equipment with those at the design stage. power, attitude control, communication, computer, and thermal subsystems performed stably and provided the satellite's normal functioning in any of its possible operational modes. No substantial failures or malfunctions were noticed either in the housekeeping of the whole bus, or in its separate modules. • All subsystems of TechSat were tested under various operational conditions. Flight experiments with ERIP were carried out only periodically for short durations. The XDEX instrument was stopped because of no correct calibration of the detector. For SUPEX, the tests were finished after 2 years because of cooler degradation. OM-2 failed after 10 months of operations. • By 2004, the digital store&forward multi-user system on TechSat was able to provide its services to the global amateur radio community. In the initial phase of the mission, there were some difficulties with the amateur BBS (Bulletin Board System) program. Considerable effort was invested to bring about the necessary changes in the satellite software to enable operation of the satellite by the radio amateur community. Table 1: Duration of TechSat subsystem operations in space Sensor complement: OM-2 (Ozone Meter-2). Objective: Measurement of the ozone concentration in the Earth's atmosphere (vertical distribution of ozone and the total ozone amount in the nadir direction). Study of latitudinal, seasonal and planetary-scale ozone variability. OM-2 is a UV spectroradiometer with a total mass of 1.80 kg (optical head of 1.55 kg and the microcontroller of 0.25 kg), "a tiny SBUV instrument," measuring in the spectral range of 252 - 340 nm. The instrument uses a filter-wheel photometer that measures the SBUV (Solar Backscattered UV) radiance. The optical sensor head consists of the following subsystems: a single lens objective, a filter wheel, a set of apertures, a baffle, and a photomultiplier detector (Rb2Te, 26 mm in diameter). The mounted objective has an aperture of 10 cm in diameter and an effective focal length of 80 mm. OM-2 conducts sequential measurements of SBUV radiation in seven wavelengths (each of 1 nm width), the sampling time is 30 ms. A total measurement sequence lasts 5 s. The total footprint size is 70 km (along-track) x 170 km (cross-track), the corresponding FOV is 3º x 12º. The data volume of one day of contiguous measurements is about 50 kByte after data compression. 12) 13) Spectral region 252 - 340 nm Number of spectral bands 7 fixed wavelengths with 1.0 nm bandwidth located at: 252.0, 273.5, 283.0, 292.2, 301.9, 320.0, 340.0 nm Measurement height of atmosphere 0 - 55 km Swath width 170 km Spatial resolution (IFOV), vertical resolution 170 km x 70 km, 5 km Precision of ozone density profile determination 10-15% Instrument mass, power 1.80 kg, 3 W Table 2: OM-2 parameter definition ERIP (Earth Remote-Sensing Imaging Package). Objective: Collection of snapshot panchromatic imagery in the vicinity of ground stations. The instrument consists of a CCD video camera unit (VCU) and an Image Processing and Control card (IPC). ERIP uses a Nikon objective, f= 135 mm, and a PUL NiX CCD TM-720. On command, a video image is captured, digitized, compressed and stored in an image buffer for later transmission. The compressed image data is transferred to the OBC (On Board Computer) and transmitted to the ground station, where the captured image is decompressed and displayed. Each image contains about 250 kByte of data, or about 60 kByte after compression. Spectral range 0.5 - 0.8 μm Spatial resolution 52 m along-track x 60 m cross-track Image size 25 km (along-track) x 31 km (cross-track) Size of CCD detector array 12 mm SNR 50 dB Light sensitivity 0.5 lux Exposure 1/60 to 1/1000 seconds Instrument mass, power, data rate 1.0 kg, 4.5 W Table 3: Instrument parameters of ERIP SOREQ (Single Event Monitor for Detecting Protons and Heavy Ions in Space). Objective: measurement of the solar charged particle environment (protons and heavy particles) for a better understanding of the changing radiation environment (interest in the hazardous nature of the environment to long-term effects on S/C electronic systems). SOREQ measures SEU (Single Event Upset) and SEL (Single Event Latch-up) occurrences in six HM65162 (2k x 8 SRAM) devices. \[Note: single-event latch-ups manifest themselves in a sudden increase of power consumption.\] The devices are arranged in two groups, allowing for the examination of chips from different date codes having different sensitivities. The TechSat computer initializes, twice per minute, a read-write circle (about 1 ms in duration) and serially reads the shift register. This enables mapping of events with a resolution of about 2º. The instrument mass is 0.23 kg, its power consumption is < 30 micro W. 14) SUPEX (Superconductivity Experiment). Objective: Conduction of a series of operational tests of the instrument in flight - consideration for later use of power generation. The superconducting device is based on thin film technology (developed at the Physics Department of Technion) made of Y1Ba2Cu3O7. It uses superconducting filters to separate the channels. The experimental assembly on-board TechSat comprises the HTS (High Temperature Superconductor) device, a cryocooler and electronic instrumentation. An automatic electronic technique is used to measure the transition temperature and critical current in the superconducting state. Cyclic measurements (about 15 minutes) are conducted once a week. The device is mounted into an insulating housing, and is thermally attached to a K-508 miniature cryocooler of Ricor, Ltd., Kibbutz Ein-Harod Ihud, Israel. The overall instrument mass is 0.63 kg, the power consumption is 12 W. The nominal cooling power is 0.5 W at 77 K. 15) 16) XDEX (X-Ray Detector Experiment). Objective: 1) test of high performance, sensitive X-ray detectors (CdZnTe) with high energy resolution; 2) test of a focal plane array where photon counting and signal processing can be performed and stored; and 3) test of degradation of the detectors/focal plane array assembly in a high-energy particle environment. The instrument consists of solid-state detectors, a sensitive preamplifier, a microcontroller and memory. The experiment is a step towards development of an X-ray telescope based on CdZnTe detectors. The instrument mass is 1.6 kg. SLRRE (Satellite Laser Ranging Retroreflector Experiment). Objective: High-precision laser ranging measurements from the ground for orbit determination (5-10 cm range). SLRRE is a passive on-board experiment consisting of an array of laser retroreflectors, corner-cube mounted on the Earth-viewing panel (panel 5) of the microsatellite. The SLRRE mass is 0.65 kg. 1) http://www.technion.ac.il/ASRI/techsat/inorbit.html 2) M. Guelman, F. Ortenberg, A. Shiryaev, R. Waller, "Microsatellites for Science and Technology: Gurwin-TechSat in-flight Experiments Results," Proceedings of the 3rd International Symposium of IAA, Berlin, April 2-6, 2001, pp. 67-70 3) http://www.amsat.org/amsat-new/satellites/satInfo.php?satID=14&retURL=/satellites/status.php 4) Information provided by Roni Waller and Fred Ortenberg of ASRI/Technion. 5) http://www.technion.ac.il/ASRI/techsat/ 6) http://www.technion.ac.il/ASRI/ 7) Information provided by Fred Ortenberg of Technion, Haifa, Israel M. Guelman, F. Ortenberg, A. Shiryaev, R. Waller, "Gurwin-TechSat Microsatellite Long-Term Mission," Proceedings of the 6th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 23 - 26, 2007 9) M. Guelman, R. Waller, A. Shiryaev, M. Psiaki, "Design and Testing of Magnetic Controllers for Satellite Stabilization," Acta Astronautica, Vol. 56, 2005, pp.231-239 10) http://www.technion.ac.il/ASRI/projects/psiaki/Psiaki.html 11) M. Guelman, F. Ortenberg, A. Shiryaev, R. Waller, "Seven-year Flight Testing of the Gurwin-Techsat Microsatellite," 19th Annual AIAA/USU Conference on Small Satellites, Utah, August 8-11, 2005, SSC05-IV-8 12) A. Devir, F. Ortenberg, ""Space-based small ultraviolet photometer for the measurement of the ozone concentration in the Earth's atmosphere," Proceedings of SPIE, Vol. 3110, 1997, pp. 161-170 13) M. Guelman, F. Ortenberg, B. Wolfson, "Flight Tests of the novel TechSat Satellite Ozone Meter: Algorithms and Measurement Processing Results," Proceedings of the 40th Israel Annual Conference of Aerospace Sciences, 2000, pp. 299-310 14) J. Barak, E. Adler, M. Murat, et al., " The SOREQ Radiation Monitor for Detecting Protons and Heavy Ions in Space and its Preliminary Flights Data on Gurwin II TechSat," Proceedings of the 14th AMSAT-UK Colloquium Space-Communication-99, University of Surrey, July 23-25, 1999, pp. 2-9 15) E. Polturak, G. Koren, et al., "Design and Performance of a Space Based High Temperature Superconductivity Experiment," Proceedings of the 14th AMSAT-UK Colloquium Space-Communication-99, University of Surrey, July 23-25, 1999, pp. 10-14 16) E. Polturak, G. Koren, M. Ayalon, "Space Based High Temperature Superconductivity Experiment," Proceedings of the 40th Israel Annual Conference of Aerospace Sciences, 2000 The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: "Observation of the Earth and Its Environment: Survey of Missions and Sensors" (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates.

][/quote]

Quelques specialités de Plasan sasa

PLASAN SUITE

Modernisation de cockpit proposé par Elbit.

Hermes 90 d'elbit system,il marche au kérosene.

je trouve que c'est trés intéréssant ce concepte :

Video presentation of Elbit Systems Closed Hatches concept including the See Through Armour system, remote control weapon stations (RCWS) and networked battle management systems (BMS). Includes footage of the UT-30 unmanned turret in operation and a representative small unit action.

Elbit Systems UT-30

Elbit Systems MUSIC

ZIBAR MK2

Galil,Tavor et Negev dans divers conditions climatiques

Rabintex,video en espagnol

y a pas dire glaive le merkava est splendide, le meilleur char au monde avec le léopard

il est taillé pour les besoins d'Israel puisque ils n'ont jamais songé l'exporté pour que ses secrets ne soient pas révélé à des ennemis d'Israel
ils doivent faire une nouvelle version export, plus légère en tonnage, chargeur automatique....

eagles a écrit:

y a pas dire glaive le merkava est splendide, le meilleur char au monde avec le léopard

Sont point faible équipage de 4 personnes ( car pas de chargement auto, comme Léo 2 d'ailleur)

Viper a écrit:

eagles a écrit:

y a pas dire glaive le merkava est splendide, le meilleur char au monde avec le léopard

Sont point faible équipage de 4 personnes ( car pas de chargement auto, comme Léo 2 d'ailleur)

Je te serai reconnaissant Viper (et à toute autre personne biensur), si tu m'expliquais en quoi est ce que l'équipage de 4 personnes peut representer un point faible pour le merkava ?!
Merci

la fatigue de l'équipage boomer ! à force les choses sont automatisé la tache devient moins pénible pour l'équipage , dans un accrochage à haute intensité il sera fort obligé de tirer au delà de 6coups/min , les minutions stockés sur tourelle vont vites être épuisée et faudra recharger