AGM-130 地导弹再探讨

先上一段我N年前收藏的洋字码，然后再说：


Boeing (Rockwell) AGM-130
The AGM-130 is a rocket-powered extended-range derivative of the GBU-15(V)/B electro-optically guided glide bomb.

     A development contract for the AGM-130 missile was awarded by the USAF to Rockwell (now Boeing) in 1984, and called for a glide-bomb equipped with a strap-on solid-propellant rocket motor. The first flight tests occurred in late 1985, but operational tests were not completed before 1989. Initial orders were placed in 1990, but in 1991 the development of some significant upgrades began. These included a new CCD seeker and a GPS/INS (GPS-aided Inertial Navigation System) mid-course guidance. According to official sources, Initial Operational Capability of the AGM-130 with the Air Force was achieved in 1994. This date probably refers to the IOC of the missiles equipped with GPS/INS and CCD seeker.

     The AGM-130 is basically a GBU-15(V)/B glide bomb with a Rocketdyne (now Alliant Techsystems) SR122-RD-1 solid-fueled rocket in a strap-on WPU-9/B propulsion section. The basic modes of operation (lock on before or after launch, two-way data link) and terminal guidance options (TV, IIR) are identical to those of the GBU-15(V)/B, q.v. for further details. After it has been dropped from the launching aircraft, the AGM-130 enters a glide flight (presumably down to the preselected cruise altitude) and then fires the rocket motor. The missile follows a low-altitude flight path, using a terrain-following system with a radar altimeter. The propulsion section is jettisoned after motor burn-out, and the missile has a range of more than 65 km (40 miles) for high-altitude and about 24 km (15 miles) for low-altitude drops. It can either fly autonomously to the target area using its GPS-aided INS, or receive updates via the data link. For terminal guidance, all versions of the AGM-130 can currently be fitted before the mission with either a WGU-40/B TV/CCD or a WGU-42/B FPA (Focal Plane Array) IIR seeker (original seekers were DSU-27B/B TV and WGU-33A/B IR). The seeker can be locked on the target before launch, during the flight, or not at all. In the latter case, the missile is either flown "manually" to the target via the data link, or will continue to the originally targeted GPS coordinates.

.      All AGM-130 variants use the "short chord"-type wings and fins of the GBU-15(V)/B, but use different types of warheads. The AGM-130A uses the 906 kg (2000 lb) MK 84 blast-fragmentation bomb, while the AGM-130B was a proposed airfield-attack version with a submunition warhead. The AGM-130B was to use a SUU-54/B dispenser with 15 BLU-106/B BKEP (Boosted Kinetic Energy Penetrator) runway-cratering and 75 Hunting HB876 area-denial submunitions, but this version was not procured. The seeker options are designated by suffix numbers, and the latest versions of the -130A are the AGM-130A-11 (TV/CCD) and AGM-130A-12 (IIR). The AGM-130C is similar to the AGM-130A, but uses a 906 kg (2000 lb) BLU-109/B penetrator warhead instead. The latest subvariants are the AGM-130C-11 with TV/CCD and AGM-130C-12 with IIR terminal homing. The AGM-130D is a variant with a BLU-118/B thermobaric warhead. Training variants of the AGM-130 family include the CATM-130A captive-carry missile and DATM-130A ground-handling training dummy.
      The first official combat use of the AGM-130 occurred during 1999 against Iraqi air-defense installations, and the missile was also used in 2001 during Operation Enduring Freedom in Afghanistan.

      Boeing also proposed and tested several extensively revised variants under the unofficial designation AGM-130E. These included a turbojet-powered extended-range version with a dual mode (TV/IIR) seeker as an entry into the British CASOM (Conventionally Armed Standoff Missile) competition, and several turbojet-powered variants with lighter warhead and/or extended capabilities. However, none of these variants was put in production.

      Between 700 and 1000 AGM-130 missiles have been procured by the U.S. Air Force, and the only current carrier aircraft for missile is the F-15E Eagle. The AGM-130 is produced by retrofit of existing GBU-15(V)/B bombs.

Specifications
Note: Data given by several sources show slight variations. Figures given below may therefore be inaccurate!

Data for AGM-130A/C:

Length 3.92 m (12 ft 10.5 in)
Wingspan 1.50 m (4 ft 11 in)
Diameter 46 cm (18 in)
Weight 1320 kg (2910 lb)
Speed high subsonic
Range > 65 km (40 miles)
Propulsion Alliant Techsystems SR122-RD-1 solid-fueled rocket
Warhead AGM-130A: 906 kg (2000 lb) MK 84 bomb
AGM-130C: 906 kg (2000 lb) BLU-109/B penetrator bomb

看不懂鸟纹。
今后再发鸟纹的，要同时发翻译稿。

发展过程:
   美国鉴于1973 年中东战争的经验，于1974年开始实施“宝石路”攻击计划，研制能在敌密集防空火力圈外投掷的GBU-15滑翔炸弹，1986年，GBU-15装备部队。1984年，开始对GBU-15加装固体火箭发动机，即研制AGM-130A型弹，1989年装备部队，成为美军实施空中防区外打击的主要武器。

发展过程:
   美国鉴于1973 年中东战争的经验，于1974年开始实施“宝石路”攻击计划，研制能在敌密集防空火力圈外投掷的GBU-15滑翔炸弹，1986年，GBU-15装备部队。1984年，开始对GBU-15加装固体火箭发动机，即研制AGM-130A型弹，1989年装备部队，成为美军实施空中防区外打击的主要武器。

作战运用:
    导弹投放后，先滑翔飞行，然后火箭发动机点火使导弹加速。发动机工作完毕或到达设定时间后，发动机分离，导弹继续滑翔飞行。到达目标区后，即将目标图像传回载机。飞行员可以根据显示的目标图像锁定目标，由导弹自行飞向目标，或者由飞行员操纵导弹去命中目标。导弹发射高度最低60米，也可中空发射，正常发射高度 200-300 米。使用穿透型战斗部的 AGM-130C ，其飞行弹道与A型不同，发射高度低于3000米，发射后火箭发动机先将导弹拉起，上升到3000米高度再巡航，到达目标上空俯冲下去攻击。这样可保证接触角约75度，穿透水泥板的厚度约3米。
　　海湾战争，美军发射了9枚AGM-130A导弹，分别由F-4和F-111挂装并发射，6枚弹直接命中目标，1枚失效。
　　科索沃战争中，美军F-15E等飞机大量使用了该型弹，在南军防空火力范围外对南境内目标实施攻击，取得了较好战绩。
识别特征：
    ①弹体首尾各加装了一组控制面，每组 4 片，对称安装。   第一组位于弹头部，翼面呈梯形，第二组位于弹尾，尺寸较大，呈矩形。
    ②弹体前细后粗，头部呈钝圆形，弹体下方加装了细于弹体的柱形火箭发动机，其长度占弹长的百分之八十左右。

性能特点：
    ①采用模块组合方法研制，便于大量生产和使用。
    ②射程远、精度高，载机安全系数高。
    ③可配备多种战斗部，攻击不同性质目标。
主要改型：
    AGM-130A。战斗采用MK84炸弹，重908千克，发射重量1323千克。
    AGM-130B。战斗部采用Suu-54子母弹箱，内装396枚BLU-97/B子弹药或混装15枚BLU-106/B 破甲子弹药和75枚杀伤地雷，重857千克，发射重量1316千克。
    AGM-130C。战斗部采用BLU-109/B穿透型炸弹，重894千克，在60度着角时，可击穿2.4米水泥板。
基本数据：
    弹重            A 型        1323 千克
                    B 型        1316 千克
    直径            A 型        406 毫米
                    B 型        510 毫米
    弹长            A 型        3.92 米
                    B 型        4.03 米
    战斗部种类      A 型        MK84 航弹
                    B 型        子弹药
                    C 型        BLU-109/B
    火箭发动机重    200 千克
    火箭发动机长    2.8 米
    射速            1 马赫
    射程            24 ～ 64 千米

回复 6# 拥抱孤独


    翻译稍后奉上，您什么时候取消插队的发言我就发...:handshake:D

我的英文水平不算高，而且网速也不太理想，目前只能先翻译4楼帖子的下半部分：

Length长度 3.92 m (12 ft 10.5 in)3.92 m(12英尺的1050)
Wingspan翼展 1.50 m (4 ft 11 in)1.50 m(4英尺11)
Diameter直径 46 cm (18 in)46厘米(18)
Weight重量 1320 kg (2910 lb)4547公斤(2910磅)
Speed速度 high subsonic高亚音速
Range范围 > 65 km (40 miles)> 65公里(40英里)
Propulsion推进 Alliant Techsystems SR122-RD-1 solid-fueled rocketTechsystems SR122-RD-1称,由于财产遭征用solid-fueled火箭发射的
Warhead弹头 AGM-130A: 906 kg (2000 lb) MK 84 bomb2000年AGM-130A:906公斤(磅)可84枚炸弹
AGM-130C: 906 kg (2000 lb) BLU-109/B penetrator bomb2000年AGM-130C:906公斤(磅)BLU-109 / B弹头炸弹

此楼层是给4楼的翻译稿预备的

太专业啦

能翻译一下吗？