超级军网美国80年代最有代表性的空空导弹方案(AIM-152A)
来源：百度文库 编辑：超级军网 时间：2024/05/03 23:10:07
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It had an inertial navigation system with dual-band semi-active radar homing for mid-course guidance and an electro-optical sensor for autonomous terminal homing.
中继制导居然是INS配合双频半主动？谁来详细说说？
中继制导居然是INS配合双频半主动？谁来详细说说？
Figures given below are estimates and/or design requirements.
如是说，还不一定是详细的设计参数啊，有可能是估计值。
如是说，还不一定是详细的设计参数啊，有可能是估计值。
雷神公司也有竞标AIM-152A的方案，不过相比西屋的方案比较土，就不用看了。
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原帖由 千羽 于 2008-10-8 10:28 发表
载机携带全向雷达吊舱，导弹发射后，载机即可转向脱离，由吊舱继续对导弹制导
怎么脱离法？吊舱还不是在载机上？
固体冲压发动机要进气口吧，没见到在什么地方……
好象记得你的这个配的图是AIM155的，这个 ...
他的意思是载机可以立刻转向脱离，此时吊舱仍然对准敌机的方向为载机提供制导。而没有吊舱的话一转向雷达就不对准敌机方向，就失去目标了。
上面有我的错误。冲压方案应该是雷神的。西屋的是多级固体火箭。
原帖由 千羽 于 2008-10-8 10:28 发表
载机携带全向雷达吊舱，导弹发射后，载机即可转向脱离，由吊舱继续对导弹制导
怎么脱离法？吊舱还不是在载机上？
固体冲压发动机要进气口吧，没见到在什么地方……
好象记得你的这个配的图是AIM155的，AIM1 ...
就这体积？:D
原帖由 千羽 于 2008-10-8 10:28 发表
载机携带全向雷达吊舱，导弹发射后，载机即可转向脱离，由吊舱继续对导弹制导
怎么脱离法？吊舱还不是在载机上？
固体冲压发动机要进气口吧，没见到在什么地方……
好象记得你的这个配的图是AIM155的，AIM1 ...
ertert老兄所给的图和数据应该来自这里 http://www.designation-systems.net/dusrm/m-152.html
YAIM-152A (Hughes/Raytheon design)和YAIM-152A (GD/Westinghouse design)
展板上的照片是Alain Ratinaud所拍摄的．
雷神的方案。
The Hughes/Raytheon AAAM was based on the ACIMD design, and used a hybrid solid-rocket/ramjet propulsion system which offered higher speeds at maximum range. It was designed to use an inertial mid-course guidance with command updates (similar to the AIM-120 AMRAAM), and a dual-mode (active-radar/infrared) seeker for terminal homing.
Specifications
No YAIM-152A missiles were ever built. Figures given below are estimates and/or design requirements.
Data for YAIM-152A:
Length 3.66 m (12 ft)
Diameter Hughes/Raytheon: 23 cm (9 in)
Weight Hughes/Raytheon: < 300 kg (660 lb)
Speed Mach 3+
Range > 185 km (100 nm)
Propulsion Hughes/Raytheon: integral rocket/ramjet engine
Warhead 14-23 kg (30-50 lb) blast-fragmentation
Main Sources
The Hughes/Raytheon AAAM was based on the ACIMD design, and used a hybrid solid-rocket/ramjet propulsion system which offered higher speeds at maximum range. It was designed to use an inertial mid-course guidance with command updates (similar to the AIM-120 AMRAAM), and a dual-mode (active-radar/infrared) seeker for terminal homing.
Specifications
No YAIM-152A missiles were ever built. Figures given below are estimates and/or design requirements.
Data for YAIM-152A:
Length 3.66 m (12 ft)
Diameter Hughes/Raytheon: 23 cm (9 in)
Weight Hughes/Raytheon: < 300 kg (660 lb)
Speed Mach 3+
Range > 185 km (100 nm)
Propulsion Hughes/Raytheon: integral rocket/ramjet engine
Warhead 14-23 kg (30-50 lb) blast-fragmentation
Main Sources
原帖由 greatmatch 于 2008-10-8 10:37 发表
他的意思是载机可以立刻转向脱离，此时吊舱仍然对准敌机的方向为载机提供制导。而没有吊舱的话一转向雷达就不对准敌机方向，就失去目标了。
那雷达吊舱中的雷达又怎么对准敌机呢？难道是能旋转的:o
另外雷达吊舱的直径有多大，能保证其雷达天线的尺寸？
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原帖由 gundam_lc_nt 于 2008-10-8 10:55 发表
那雷达吊舱中的雷达又怎么对准敌机呢？难道是能旋转的:o
另外雷达吊舱的直径有多大，能保证其雷达天线的尺寸？
中国人应该很聪明的啊。
能够发明以地制空、变后掠翼超巡。雷达吊舱的旋转问题，也应该能解决的。
原帖由 我立于高山之巅 于 2008-10-8 10:57 发表
AIM-155的射程相对来说要比152大出一半左右，但是intended weight依然保持在300-340公斤。
那西屋的东西射程可能就达不到180了。
AIM-155 Advanced Air-to-Air Missile (AAAM)
Development
The AIM-155 Advanced Air-to-Air Missile (AAAM) was a programme to develop a successor to the Hughes AIM-54 Phoenix. The US Naval Weapons Center began a two to three year technology validation programme in early 1982, with simulations, intended to lead to hardware tests, including trials with complete guided missiles. The AIM-155 should have been much smaller and would have less airframe impact than the AIM-54 without giving up performance. The range should have been 270 km, the speed Mach four, the diameter 229 mm and the warhead would have a weight of 13.6 to 22.7 kg. The AIM-155 would have been lighter than the AIM-54, which has a weight of 446 kg (AIM-54A) or 465 kg (AIM-54C), so the intended weight was 300 kg. The AIM-155 was intended for (improved variants of) the Grumman F-14 Tomcat of the US Navy. The F-14 would have been able to land back on an aircraft carrier while it carried eight AAAMs rather than four AIM-54s at present.
The US Congress wanted that this US Navy programme became a combined US Navy and US Air Force (USAF) programme, but the official USAF position was that the service had no requirement for an extended-range air-to-air missile, so it was confining its role to that of monitoring the programme. If a requirement would emerge, the AIM-155 would be purchased and could have armed the McDonnell Douglas F-15C/D Eagle and the Lockheed Martin/Boeing F-22A Raptor. The AIM-155 would have had a much better capability against stealth aircraft than the AIM-120 AMRAAM. This very promissing programme was cancelled in 1992.
Contenders
The development of the AIM-155 started in 1988 with the award of contracts to two industrial teams, General Dynamics with Westinghouse and Hughes with Raytheon and McDonnell Douglas. The two teams have taken different technical approaches for the development of the AIM-155.
General Dynamics/Westinghouse
General Dynamics and Westinghouse proposed a missile with a multiple-pulse solid rocket motor and a dual semi-active radar/electro-optical (EO) guidance system. This proposal used a small missile in a powered launch tube to increase reliability and a wing-mounted targeting pod with a radar fore and aft of the pod, so that the launch aircraft did not have to fly in the direction of the target. The pod would have a weight of 340 kg and the dimensions of the pod would have been 406 mm x 3,607 mm. Shortly after the launch, the wings extended and after a few seconds the launch tube fell away. The AIM-155 used mid-course guidance, just like the AIM-120 AMRAAM, and in the neighbourhood of the target, the radar became active. If the target would use ECM, the AIM-155 would target on the ECM signals. There was also an infra-red (IR) seeker in case the guidance would fail. The use of all known kinds of targeting systems would make the AIM-155 invincible. The AIM-155 could also have been carried by small (V/STOL) multi-purpose aircraft. This design was based on the Advanced Missile System (AMS), a proposed weapon which General Dynamics studied for a decade. The weight would have been 172 kg and the dimensions 140 mm x 3,658 mm.
Hughes/Raytheon/McDonnell Douglas
The development of the AIM-155 began with an in-house development of Raytheon, called Advanced Intercept Air-to-Air Missile (AIAAM), and revealed in the form of a one-third scale model at the US Navy League 1982 Convention. The AIAAM had an aircraft configuration, with one set of wings and tail controls for twist-and-steer manoeuvring. An inclined supersonic inlet under the belly feeded an advanced ramjet of a hybird propulsion system. One possible propulsion contracter was CSD, who also provided a hybird (rocket/ramjet) propulsion system for the Firebolt. CSD also provided the integral ramjet for the Vought Supersonic Tactical Missile (STM), a long-range research missile for the US Navy, and ducted rockets for other missiles. The AIAAM had thus a wide choice of propulsion systems, and it was hoped to lead the way to the air-to-air member of the planned new family of air-breathing supersonic missiles offering enormously enhanced range and sustained high power of manoeuvre.
A consortium of Hughes, Raytheon and McDonnell Douglas proposed a missile powered by a hybird propulsion system consisting of a ramjet and a solid rocket booster. This form of propulsion would provide a slower acceleration than the rocker propulsion system of General Dynamics and Westinghouse, but the benefit would come at ranges beyond two-thirds of the maximum range when the ramjet powered missile would have been faster. The AIM-155 used mid-course guidance, just like the AIM-120 AMRAAM, and in the neighbourhood of the target a dual-mode active radar/infra-red (IR) guidance system would have been used. The length would have been 3,658 mm.
Sources
An Illustrated Guide to Modern Airborne Missiles, Bill Gunston, Salamander Books Limited, 1983.
E-mail from Ragnar Emsoy (emsoy@hotmail.com).
E-mail from Christopher S. Liu (csl@hprnd.rose.hp.com).
E-mail from Craig Paffhausen (nimitz@megsinet.net).
Is de F-22 zijn geld waard?, Steven Bolt, Kijk, September 1991.
Stealth Warplanes - Deception, Evasion and Concealment in the Air, Doug Richardson, Salamander Books Limited, 1989.
US Navy & Marine Corps Air Power Directory, David Donald and Jon Lake, Aerospace Publishing Limited, 1996.
Ruud Deurenberg, 17 September 1998
Development
The AIM-155 Advanced Air-to-Air Missile (AAAM) was a programme to develop a successor to the Hughes AIM-54 Phoenix. The US Naval Weapons Center began a two to three year technology validation programme in early 1982, with simulations, intended to lead to hardware tests, including trials with complete guided missiles. The AIM-155 should have been much smaller and would have less airframe impact than the AIM-54 without giving up performance. The range should have been 270 km, the speed Mach four, the diameter 229 mm and the warhead would have a weight of 13.6 to 22.7 kg. The AIM-155 would have been lighter than the AIM-54, which has a weight of 446 kg (AIM-54A) or 465 kg (AIM-54C), so the intended weight was 300 kg. The AIM-155 was intended for (improved variants of) the Grumman F-14 Tomcat of the US Navy. The F-14 would have been able to land back on an aircraft carrier while it carried eight AAAMs rather than four AIM-54s at present.
The US Congress wanted that this US Navy programme became a combined US Navy and US Air Force (USAF) programme, but the official USAF position was that the service had no requirement for an extended-range air-to-air missile, so it was confining its role to that of monitoring the programme. If a requirement would emerge, the AIM-155 would be purchased and could have armed the McDonnell Douglas F-15C/D Eagle and the Lockheed Martin/Boeing F-22A Raptor. The AIM-155 would have had a much better capability against stealth aircraft than the AIM-120 AMRAAM. This very promissing programme was cancelled in 1992.
Contenders
The development of the AIM-155 started in 1988 with the award of contracts to two industrial teams, General Dynamics with Westinghouse and Hughes with Raytheon and McDonnell Douglas. The two teams have taken different technical approaches for the development of the AIM-155.
General Dynamics/Westinghouse
General Dynamics and Westinghouse proposed a missile with a multiple-pulse solid rocket motor and a dual semi-active radar/electro-optical (EO) guidance system. This proposal used a small missile in a powered launch tube to increase reliability and a wing-mounted targeting pod with a radar fore and aft of the pod, so that the launch aircraft did not have to fly in the direction of the target. The pod would have a weight of 340 kg and the dimensions of the pod would have been 406 mm x 3,607 mm. Shortly after the launch, the wings extended and after a few seconds the launch tube fell away. The AIM-155 used mid-course guidance, just like the AIM-120 AMRAAM, and in the neighbourhood of the target, the radar became active. If the target would use ECM, the AIM-155 would target on the ECM signals. There was also an infra-red (IR) seeker in case the guidance would fail. The use of all known kinds of targeting systems would make the AIM-155 invincible. The AIM-155 could also have been carried by small (V/STOL) multi-purpose aircraft. This design was based on the Advanced Missile System (AMS), a proposed weapon which General Dynamics studied for a decade. The weight would have been 172 kg and the dimensions 140 mm x 3,658 mm.
Hughes/Raytheon/McDonnell Douglas
The development of the AIM-155 began with an in-house development of Raytheon, called Advanced Intercept Air-to-Air Missile (AIAAM), and revealed in the form of a one-third scale model at the US Navy League 1982 Convention. The AIAAM had an aircraft configuration, with one set of wings and tail controls for twist-and-steer manoeuvring. An inclined supersonic inlet under the belly feeded an advanced ramjet of a hybird propulsion system. One possible propulsion contracter was CSD, who also provided a hybird (rocket/ramjet) propulsion system for the Firebolt. CSD also provided the integral ramjet for the Vought Supersonic Tactical Missile (STM), a long-range research missile for the US Navy, and ducted rockets for other missiles. The AIAAM had thus a wide choice of propulsion systems, and it was hoped to lead the way to the air-to-air member of the planned new family of air-breathing supersonic missiles offering enormously enhanced range and sustained high power of manoeuvre.
A consortium of Hughes, Raytheon and McDonnell Douglas proposed a missile powered by a hybird propulsion system consisting of a ramjet and a solid rocket booster. This form of propulsion would provide a slower acceleration than the rocker propulsion system of General Dynamics and Westinghouse, but the benefit would come at ranges beyond two-thirds of the maximum range when the ramjet powered missile would have been faster. The AIM-155 used mid-course guidance, just like the AIM-120 AMRAAM, and in the neighbourhood of the target a dual-mode active radar/infra-red (IR) guidance system would have been used. The length would have been 3,658 mm.
Sources
An Illustrated Guide to Modern Airborne Missiles, Bill Gunston, Salamander Books Limited, 1983.
E-mail from Ragnar Emsoy (emsoy@hotmail.com).
E-mail from Christopher S. Liu (csl@hprnd.rose.hp.com).
E-mail from Craig Paffhausen (nimitz@megsinet.net).
Is de F-22 zijn geld waard?, Steven Bolt, Kijk, September 1991.
Stealth Warplanes - Deception, Evasion and Concealment in the Air, Doug Richardson, Salamander Books Limited, 1989.
US Navy & Marine Corps Air Power Directory, David Donald and Jon Lake, Aerospace Publishing Limited, 1996.
Ruud Deurenberg, 17 September 1998
The range should have been 270 km, the speed Mach four, the diameter 229 mm and the warhead would have a weight of 13.6 to 22.7 kg. The AIM-155 would have been lighter than the AIM-54, which has a weight of 446 kg (AIM-54A) or 465 kg (AIM-54C), so the intended weight was 300 kg.
果然是天顶星科技。
果然是天顶星科技。
There was also an infra-red (IR) seeker in case the guidance would fail.
而且这些超远程AAM貌似都在考虑光学导引头，我不理解那是怎么解决导引头外罩形状的，一般IR制导都是钝首，高速飞行阻力很大，棱锥形的西北风已属罕见，难不成学SM-3搞侧窗？以前有个使用M-2000的IR导引头的R-77改进型想象图，看起来大囧，基本就是一格斗弹的感觉。
而且这些超远程AAM貌似都在考虑光学导引头，我不理解那是怎么解决导引头外罩形状的，一般IR制导都是钝首，高速飞行阻力很大，棱锥形的西北风已属罕见，难不成学SM-3搞侧窗？以前有个使用M-2000的IR导引头的R-77改进型想象图，看起来大囧，基本就是一格斗弹的感觉。
回楼上的,可抛头罩~~~~~~~~~~
原帖由 ertert 于 2008-10-8 10:59 发表
中国人应该很聪明的啊。
能够发明以地制空、变后掠翼超巡。雷达吊舱的旋转问题，也应该能解决的。
[:a1:] 用这个吊舱的不是美国货吗？我想知道老美是怎么解决这个问题的。
原帖由 pighead 于 2008-10-8 11:10 发表
回楼上的,可抛头罩~~~~~~~~~~
看来VL MICA有个老前辈啊。
原帖由 gundam_lc_nt 于 2008-10-8 11:11 发表
[:a1:] 用这个吊舱的不是美国货吗？我想知道老美是怎么解决这个问题的。
那只有问老美或者老大了，俺们菜鸟也不懂啊。
AAAM项目的基本要求是射程185以上,达不到这个指标的方案不会参与竞争的.
就是100nm，美国人喜欢凑整。
原帖由 gundam_lc_nt 于 2008-10-8 10:55 发表
那雷达吊舱中的雷达又怎么对准敌机呢？难道是能旋转的:o
另外雷达吊舱的直径有多大，能保证其雷达天线的尺寸？
要不怎么叫全向呢？具体细节就不知道啦。反正他说的全向就是这个意思。
记得还有个AIM154，重量只有172千克，射程270千米。
补上几个图.
在原来挂1枚AIM-54的空间,两种AAAM分别可挂3枚和1枚.
原帖由 ertert 于 2008-10-8 09:38 发表
AAAM的方案之一。西屋公司参与AIM-152A竞标的方案：
1、固体冲压发动机
2、蛋载主动相控阵雷达
3、雷达和红外双模导引头
4、矢量推力，可作为格斗蛋使用
5、接近AIM-120的重量，提供超过180公里的有效射程
6、 ...
80年代上马，没造出样蛋，92年下马。欧洲流星相比也是小儿科。---------------------------------------------------------------------------------------------------连样弹都没造出来还说流星是小儿科？！哈美不是这么哈的！！:D
原帖由 我立于高山之巅 于 2008-10-8 11:13 发表
看来VL MICA有个老前辈啊。
也有不用可抛头罩硬抗的,比如r27et~~~~~~~~~:D
原帖由 pighead 于 2008-10-8 13:47 发表
也有不用可抛头罩硬抗的,比如r27et~~~~~~~~~:D
毛人似乎比较喜欢硬抗，R-77T就是这么个东西。貌似M-2000 性能不错，比M-80好多了。不过好像从来没说R-27ET比ER速度慢的，一般都说射程小。
GLA的远程蛋，可惜...
原帖由 greatmatch 于 2008-10-8 11:55 发表
要不怎么叫全向呢？具体细节就不知道啦。反正他说的全向就是这个意思。
我觉得仅仅这一个“全向”就够老美喝一壶的了。实际仔细想想别说那个时候，就是现在在一定体积要求下弄出这种全向的雷达吊舱也不是容易的事情。所以这个蛋蛋弄不出来（指弄出来并达到当初的设计要求）是显然的。
原帖由 gundam_lc_nt 于 2008-10-13 13:51 发表
我觉得仅仅这一个“全向”就够老美喝一壶的了。实际仔细想想别说那个时候，就是现在在一定体积要求下弄出这种全向的雷达吊舱也不是容易的事情。所以这个蛋蛋弄不出来（指弄出来并达到当初的设计要求）是显然的。
不说这个雷达吊舱，仅仅远程AAM，实际上其存在的意义就不太大，基本就是截击机配备，一般的空优机不会用这个，就算是270KG，这种重量，在最大射程附近，很难保证足够的机动能力，再说超远距目标的识别等一系问题，所以说，基本上，自从美国空军取消了专用防空战斗机后，就对远程AAM再没感兴趣过，倒是美国海军，因为在大海上，面临前苏联的TU22M，以及如果苏联没有解体，肯定会出现的海上攻击型的TU160，对这类远程AAM一直很感兴趣。大海上，因为没有陆地的杂波，机上雷达，比较容易解决超远距目标的识别和稳定跟踪，而且因为主要对付机动能力不佳的轰炸机和远程反舰巡航导弹，能比较好的利用远程AAM的最大射程。
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载机携带全向雷达吊舱，导弹发射后，载机即可转向脱离，由吊舱继续对导弹制导.
这句很外行，就不驳斥了。
这句很外行，就不驳斥了。
载机携带全向雷达吊舱，导弹发射后，载机即可转向脱离，由吊舱继续对导弹制导. 这句很外行，就不驳斥了 ...
请教，怎么个外行了？
请教，怎么个外行了？
谁也没规定吊舱里只有一个天线呀，全向不是问题。
还有，脱离的意思根本不是掉头就跑，改变拉近势态保持安全位置而已，否则就可能放弃跟踪了，这怎么可以？
还有，脱离的意思根本不是掉头就跑，改变拉近势态保持安全位置而已，否则就可能放弃跟踪了，这怎么可以？
两级式空空导弹有什么优缺点？
雷达吊舱孔径如果不大，对RCS为3平方米的目标就不可能有185KM以上的有效跟踪距离，连100KM的有效跟踪距离都很成问题
，但如果吊舱孔径够大，又会带来飞行阻力大增，造成机动性能的大幅下降。
，但如果吊舱孔径够大，又会带来飞行阻力大增，造成机动性能的大幅下降。