Lực lượng phòng vệ Nhật Bản - 日本国自衛隊- The Japan Self Defence Forces

AIM-7M




The AIM-7 Sparrow missile (AIM - Aerial Intercept Missile) has been the premier medium range air-to-air missile for the US Air Force since entering production in 1972. In the Gulf War, the AIM-7 Sparrow proved to be a very potent air-to-air weapon. 22 Iraqi fixed-wing aircraft and three Iraqi helicopters were downed by radar-guided AIM-7 Sparrow missiles.
The AIM-7 is a typical loadout on F-15 air-superiority versions (F-15A/C) but is a rarely seen weapon on F-15E Strike Eagle aircraft.
Only when used on rather uncommon air-superiority missions, the F-15E carries the AIM-7 on its CFTÂs internal weapons rows. Up to four AIM-7 missiles can be attached to the aircraftÂs weapons stations LCT-1/LCT-3 and RCT-1/RCT-3 in combination with the LAU-106 ejector launcher. The AIM-7 is too heavy to be launched from the underwing LAU-128/A rail launchers.
The F-15E uses the AIM-7M missile, which entered service in 1982, and the improved AIM-7P missile, which is currently built by new production as well as conversion of existing AIM-7M missiles.
The AIM-7M version has an inverse monopulse semi-active seeker which, with digital processing, greatly improves the missileÂs performance under heavy ECM and weather con***ions. It also has the advantage of an active radar fuze, which together with the built-in test system has provided a more reliable missile, capable of attacking low-flying aircraft targets.
The AIM-7P missile has improved guidance electronics, a new fuze and an onboard computer with twice the capacity and speed of the current models. It also has the capability to receive mid-course uplink information in the same formats used by the AIM-54 Phoenix, AIM-120 AMRAAM and AGM-78 Standard missiles.
www.f-15estrikeeagle.com

The semi-active AIM-7 guides on RF energy radiated by the F-15Ês AN/APG-70 Radar and deflected by the enemy aircraft. During its supersonic boost-and-glide flight, the missile receives radar data from the F-15Ês fire control system via its rear signal receiver and also receives reflected RF energy from the target via its own internal radar receiver (front signal).
The incoming signals from both the rear receiver and the front radar receiver is processed by the Missile Borne Computer (MBC) located in the guidance section of the missile. A comparison of these signals allows the MBC to sence changes in target position and create signals used by the autopilot, located in the control section, to control movement of the wings and thus maintain course to target intercept.
The autopilot sends guidance command signals to the hydraulic control group. The hydraulic control group uses the hydraulic power supplied by an accumulator to move the four delta platform wings located on the hub assembly of the control section in response to the guidance command signals from the autopilot.
www.f-15estrikeeagle.com

The missileÂs wings guide the missile toward the "point of intercept" and stabilize the missile in pitch, yaw, and roll. Missile stability is also provided by four fixed delta fins, which are located on the rear of the missile in line with the forward wings.
The blast fragmentation type warhead assembly is located between the guidance section and the control section. The Save-Arm-Device (SAD) in the warhead assembly is electrically connected with the guidance section by a SAD cable. At the nearest point of intercept, the active RF fuzing circuit in the guidance sections sends a fuze pulse to the warheadÂs SAD, which ignites the fuze booster. The fuze booster detonates and finally ignites the main warhead charge. Detonation is also triggered by an impact switch located in the control section.
The AIM-7M/P missile has a WDU-27/B fixed-focus blast fragmentation warhead with a metal casing around the explosive charge. The inside of the metal casing is notched to provide the necessary amount of shrapnel.
The AIM-7 missile incorporates Electronic-Counter-Countermeasure (ECCM) capabilities, also known as Electronic Protection (EP), to defeat countermeasures by the target such as jamming.
www.f-15estrikeeagle.com

AIM-9L

AIM-9B, AIM-9D, AIM-9C

The AIM-9 Sidewinder is the world''s most successful short-range air-to-air missile, and will remain the U.S. military''s main "dogfight" AAM for the foreseeable future.
Development of Sidewinder began in 1950 at the NOTS (Naval Ordnance Test Station) - later renamed as NWC (Naval Weapons Center) - at China Lake. The idea was to create a very simple heat-seeking air-to-air missile by equipping a 12.7 cm (5 in) air-to-air rocket with a lead sulphide (PbS) photo cell in a hemispherical glass nose to detect IR radiation. Another simple, yet effective, idea was the use of "Rollerons" (sliptream-driven wheels at the fin trailing edges acting as stabilizing gyros) as roll-stabilizing devices. The first test missiles were fired in 1951, and on 11 September 1953, the first air-to-air hit on a drone was scored. In the same year, the prototype missile received the offical designation XAAM-N-7.
General Electric began low-rate production in 1955, and in May 1956, the AAM-N-7 Sidewinder I entered U.S. Navy service. Only 240 Sidewinder I missiles were built, and full-rate production missiles (built by Ford Aerospace (Philco) and General Electric) were known as AAM-N-7 Sidewinder IA. I have found no evidence that the AAM-N-7 designations ever used suffix letters (like AAM-N-7a, etc.). For ease of reference, I will use the post-1963 designations of AIM-9A (Sidewinder I) and AIM-9B (Sidewinder IA) throughout this text, even when referring to pre-1963 events.
www.designation-systems.net

CĂi này nhơn hao hao 'ỏằ" Nga nhỏằ? (cĂi cĂnh trặỏằ>c), copy hay hỏằÊp tĂc gơ không ? .
CĂi bĂc này câng "trạm" thỏưt, quỏng mỏằTt mỏằ> tiỏng Anh lỏôn tiỏng Nhỏưt, tuyỏằn không có 1 chỏằ tiỏng Viỏằ?t. Ngon hặĂn nỏằa, lỏĂi chặĂi tiỏp tiỏng Bỏằ" Đào Nha . Nói thỏưt, nghi ngỏằ khỏÊ nfng "'a ngôn ngỏằ" cỏằĐa bĂc này quĂ. KhỏÊ nfng thỏưt hay làm oai 'Ây ???

The AIM-9A/B used a 4.5 kg (10 lb) blast-fragmentation warhead. This was triggered by an IR proximity or contact fuze, and had an effective kill radius of about 9 m (30 ft). The uncooled PbS seeker of these early missiles had a 4Â angle of view and a tracking rate of 11Â/s, and the missile itself could turn at 12G. Propulsion was provided by a Thiokol MK 17 solid-fuel rocket motor (17.8 kN (4000 lb) thrust for 2.2 s), which could propel the missile to a speed of Mach 1.7 above launch speed. Because of the limitations of the seeker, the AIM-9A/B could only be used for tail-on engagements of non-manoeuvering(!) targets at ranges between 900 m (3000 ft) and 4.8 km (2.6 nm). The missile was also very susceptible to other heat sources (sun, ground reflections).
Because of the usual inter-service rivalry, the USAF did not adopt the Sidewinder, until a "fly-off" against the USAF''s GAR-2/AIM-4B Falcon in June 1955 showed the superiority of the Sidewinder. The USAF subsequently procured the AIM-9B under the designation GAR-8. More than 80000 AIM-9B missiles were produced until 1962.
On 24 September 1958, the Sidewinder achieved the world''s first successful use of air-to-air guided missiles, when Taiwanese F-86Fs shot down Communist Chinese MiG-15s using AIM-9Bs supplied by the U.S. Navy.

The limited performance of the AIM-9B prompted the Navy to look for improvements. The AAM-N-7 Sidewinder IC was developed in two version: a semi-active radar homing version (called Sidewinder IB in source [1]), designated AIM-9C in 1963, and an IR guided version, later designated as AIM-9D. Improvements common to both IC versions include a new Hercules MK 36 solid-fuel rocket motor for significantly increased speed and 18 km (9.7 nm) range, a larger MK 48 continuous-rod warhead, and slightly larger fins.
www.designation-systems.net

The SARH AIM-9C was only used with the Navy''S F8U Crusader fighters to provide these with an all-weather capability without having to fit a Sparrow-compatible radar. However, the AIM-9C was not very successful, and only 1000 were built by Motorola between 1965 and 1967. Many were later converted into AGM-122A Sidearm anti-radiation missiles.
The IR seeker of the AIM-9D (in a more pointed nose) featured a new nitrogen-cooled PbS seeker, which had field of view of only 2.5Â (reduced background noise) and a higher traking rate of 12Â/s. However, only about 1000 AIM-9D missiles were built (by Philco-Ford and Raytheon) between 1965 and 1969.
The following table summarizes the redesignations of the Sidewinder variants in June 1963:
Old Designation New Designation
AAM-N-7 Sidewinder I AIM-9A
AAM-N-7 Sidewinder IA
GAR-8 AIM-9B
AAM-N-7 Sidewinder IC (SARH) AIM-9C
AAM-N-7 Sidewinder IC (IR) AIM-9D
www.designation-systems.net

Trích từ bài ongtom
Cái này nhìn hao hao đồ Nga nhỉ (cái cánh trước), copy hay hợp tác gì không ? .
Cái bác này cũng "trùm" thật, quẳng một mớ tiếng Anh lẫn tiếng Nhật, tuyền không có 1 chữ tiếng Việt. Ngon hơn nữa, lại chơi tiếp tiếng Bồ Đào Nha . Nói thật, nghi ngờ khả năng "đa ngôn ngữ" của bác này quá. Khả năng thật hay làm oai đây ???
BOx kỹ thuật sao bạn hỏi mình trình độ làm gì vậy, vớ vẫn
Mình có ghi nguồn và cũng ko nói mình thông minh , nên bạn thông cảm
Được alphandt sửa chữa / chuyển vào 23:37 ngày 30/05/2009
Được alphandt sửa chữa / chuyển vào 23:39 ngày 30/05/2009
Được alphandt sửa chữa / chuyển vào 23:40 ngày 30/05/2009
Được alphandt sửa chữa / chuyển vào 23:42 ngày 30/05/2009

ASM 1
The Japanese Type 80 ASM-1 Missile is designed primarily as an air-launched coastal defense weapon. In practice it could be used against a variety of surface targets, including ships, truck convoys, light armored vehicles, buildings and bridges. With the ad***ion of a solid-fuel booster stage, this missile is also used as part of the ground-launched SSM-1 system.
Based on the Type-80 Air-to-Ship Missile, various anti-ship systems including Type-88 SSM (Surface-to-Ship Missile), Type-90 SSM (Ship-to-Ship Missile), Type-91 and 93 ASMs (Air-to-Ship Missile) have been developed. These systems comprise the Japanese anti-ship missile family and are deployed in the Ground, Maritime, and Air Self Defense Forces.
Contractor Mitsubishi Heavy Industries
Entered Service 1980
Total length 4.0 m
Diameter 0.35 m
Wingspan 1.2 m
Weight 600 kg
Warhead 150kgHE semi-armor piercing
Propulsion solid
Maximum Speed
Maximum effective range 50 km
Guidance mode Inertial + active radar
Single-shot hit probability
www.fas.org